Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -9A, -11, -15, and -17 Turbofan Engines, 39582-39584 [E9-18941]

Download as PDF 39582 Federal Register / Vol. 74, No. 151 / Friday, August 7, 2009 / Proposed Rules actions required by the Secretary (unless otherwise provided in applicable agreements). Except as provided in § 609.15, no party may waive or relinquish, without the consent of the Secretary, any collateral securing the Guaranteed Obligation to which the United States would be subrogated upon payment under the Loan Guarantee Agreement. (b) In the event of a default, the Secretary may enter into such contracts as the Secretary determines are required to preserve the collateral. The cost of such contracts may be charged to the Borrower. pwalker on DSK8KYBLC1PROD with PROPOSALS § 609.17 Audit and Access to Records. (a) The Loan Guarantee Agreement and related documents shall provide that: (1) The Eligible Lender, or DOE in conjunction with the Federal Financing Bank where loans are funded by the Federal Financing Bank or other Holder or other party servicing the Guaranteed Obligations, as applicable, and the Borrower, shall keep such records concerning the project as is necessary, including the Pre-Application, Application, Term Sheet, Conditional Commitment, Loan Guarantee Agreement, Credit Agreement, mortgage, note, disbursement requests and supporting documentation, financial statements, audit reports of independent accounting firms, lists of all project assets and non-project assets pledged as security for the Guaranteed Obligations, all off-take and other revenue producing agreements, documentation for all project indebtedness, income tax returns, technology agreements, documentation for all permits and regulatory approvals and all other documents and records relating to the Eligible Project, as determined by the Secretary, to facilitate an effective audit and performance evaluation of the project; and (2) The Secretary and the Comptroller General, or their duly authorized representatives, shall have access, for the purpose of audit and examination, to any pertinent books, documents, papers and records of the Borrower, Eligible Lender or DOE or other Holder or other party servicing the Guaranteed Obligation, as applicable. Such inspection may be made during regular office hours of the Borrower, Eligible Lender or DOE or other Holder, or other party servicing the Eligible Project and the Guaranteed Obligations, as applicable, or at any other time mutually convenient. (b) The Secretary may from time to time audit any or all items of costs included as Project Costs in statements VerDate Nov<24>2008 16:10 Aug 06, 2009 Jkt 217001 or certificates submitted to the Secretary or the servicer or otherwise, and may exclude or reduce the amount of any item which the Secretary determines to be unnecessary or excessive, or otherwise not to be an item of Project Costs. The Borrower will make available to the Secretary all books and records and other data available to the Borrower in order to permit the Secretary to carry out such audits. The Borrower should represent that it has within its rights access to all financial and operational records and data relating to Project Costs, and agrees that it will, upon request by the Secretary, exercise such rights in order to make such financial and operational records and data available to the Secretary. In exercising its rights hereunder, the Secretary may utilize employees of other Federal agencies, independent accountants, or other persons. § 609.18 Deviations. To the extent that such requirements are not specified by the Act or other applicable statutes, DOE may authorize deviations on an individual request basis from the requirements of this part upon a finding that such deviation is essential to program objectives and the special circumstances stated in the request make such deviation clearly in the best interest of the Government. DOE will consult with OMB and the Secretary of the Treasury before DOE grants any deviation that would constitute a substantial change in the financial terms of the Loan Guarantee Agreement and related documents. Any deviation, however, that was not captured in the Credit Subsidy Cost will require either additional fees or discretionary appropriations. A recommendation for any deviation shall be submitted in writing to DOE. Such recommendation must include a supporting statement, which indicates briefly the nature of the deviation requested and the reasons in support thereof. [FR Doc. E9–18810 Filed 8–6–09; 8:45 am] BILLING CODE 6450–01–P PO 00000 Frm 00018 Fmt 4702 Sfmt 4702 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2009–0317; Directorate Identifier 79–ANE–18] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney JT8D–7, –7A, –7B, –9, –9A, –11, –15, and –17 Turbofan Engines AGENCY: Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). SUMMARY: The FAA proposes to supersede an existing airworthiness directive (AD) for Pratt & Whitney JT8D–1, –1A, –1B, –7, –7A, –7B, –9, –9A, –11, –15, and –17 turbofan engines with 2nd stage fan blades, part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402 installed. That AD currently requires initial and repetitive ultrasonic inspection (UI) and fluorescent penetrant inspection (FPI) of those P/N 2nd stage fan blades. This proposed AD would replace the required FPI with eddy current inspection (ECI) on all affected 2nd stage fan blades and would maintain the requirement of ultrasonic inspection (UI) of the blade root attachment on some of the affected 2nd stage fan blades. This proposed AD would also introduce an optional terminating action to the repetitive blade inspections for certain engine models. This proposed AD results from reports of 10 fractures of 2nd stage fan blades since AD 87–14– 01R1 became effective. We are proposing this AD to prevent uncontained failure of 2nd stage fan blades, which could result in damage to the airplane. DATES: We must receive any comments on this proposed AD by October 6, 2009. ADDRESSES: Use one of the following addresses to comment on this proposed 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. E:\FR\FM\07AUP1.SGM 07AUP1 Federal Register / Vol. 74, No. 151 / Friday, August 7, 2009 / Proposed Rules FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117, fax (781) 238–7199. SUPPLEMENTARY INFORMATION: pwalker on DSK8KYBLC1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments regarding this proposal. Send your comments to an address listed under ADDRESSES. Include ‘‘Docket No. FAA– 2009–0317; Directorate Identifier 79– ANE–18’’ in the subject line of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of the proposed AD. We will consider all comments received by the closing date and may amend the proposed AD in light of those comments. 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 proposed 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 proposed 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. Discussion The FAA proposes to amend 14 CFR part 39 by superseding AD 87–14–01 R1, Amendment 39–6359 (54 FR 43954, October 30, 1989). That AD requires initial and repetitive UI and FPI of P/N 433802, 645902, 759902, 695932, VerDate Nov<24>2008 16:10 Aug 06, 2009 Jkt 217001 678102, and 746402 2nd stage fan blades. That AD was the result of reports of on-going fractures of 2nd stage fan blades since 1980. That condition, if not corrected, could result in uncontained failure of 2nd stage fan blades, which could result in damage to the airplane. Actions Since AD 87–14–01 R1 Was Issued Since AD 87–14–01 R1 was issued, Pratt & Whitney has developed and published an ECI procedure for inspecting the 2nd stage fan blade pinroot holes. We have reviewed this procedure and determined that mandating this ECI procedure will result in an increased level of safety for the affected engines. FAA’s Determination and Requirements of the Proposed AD We have evaluated all pertinent information and identified an unsafe condition that is likely to exist or develop on other products of this same type design. For that reason, we are proposing this AD, which would require, for 2nd stage fan blades P/Ns 678102 and 746402, an ECI of the blade pin-root holes for cracks, and for 2nd stage fan blades P/Ns 433802, 645902, 759902, and 695932, an ECI of the blade pin-root holes and UI the blade root attachment for cracks. This proposed AD would also eliminate the JT8D–1, –1A, and –1B engines from the applicability, because those engine models have either been converted to other affected engine models included in the proposed AD or retired from service. Costs of Compliance We estimate that this proposed AD would affect 1,380 engines installed on airplanes of U.S. registry. We also estimate that it would take about 25 work-hours per engine to perform one inspection cycle, and that the average labor rate is $80 per work-hour. Based on these figures, we estimate the total cost of the proposed AD to U.S. operators to be $2,760,000. 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 PO 00000 Frm 00019 Fmt 4702 Sfmt 4702 39583 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 the proposed 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. Would 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 regulatory evaluation of the estimated costs to comply with this proposed AD. See the ADDRESSES section for a location to examine the regulatory evaluation. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Safety. The Proposed Amendment Under the authority delegated to me by the Administrator, the Federal Aviation Administration proposes to amend 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 39–6359 (54 FR 43954, October 30, 1989) and by adding a new airworthiness directive to read as follows: Pratt & Whitney: Docket No. FAA–2009– 0317; Directorate Identifier 79–ANE–18. Comments Due Date (a) The Federal Aviation Administration (FAA) must receive comments on this E:\FR\FM\07AUP1.SGM 07AUP1 39584 Federal Register / Vol. 74, No. 151 / Friday, August 7, 2009 / Proposed Rules airworthiness directive (AD) action by October 6, 2009. Affected ADs (b) This AD supersedes AD 87–14–01 R1, Amendment 39–6359. Applicability (c) This AD applies to Pratt & Whitney JT8D–7, –7A, –7B, –9, –9A, –11, –15, and –17 turbofan engines, with 2nd stage fan blades, part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, installed. These engines are installed on, but not limited to, Boeing 727, 737, and McDonnell Douglas DC–9 series airplanes. Unsafe Condition (d) This AD results from reports of 10 fractures of 2nd stage fan blades since AD 87–14–01R1 became effective. We are issuing this AD to prevent uncontained failure of 2nd stage fan blades, which could result in 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. pwalker on DSK8KYBLC1PROD with PROPOSALS 2nd Stage Fan Blade Inspections (f) For 2nd stage fan blades, P/N 678102 and P/N 746402, perform an eddy current inspection (ECI) of the blade pin-root holes for cracks, and for 2nd stage fan blades, P/Ns 433802, 645902, 759902, and 695932, perform an ECI of the blade pin-root holes and perform an ultrasonic inspection (UI) of the blade root attachment for cracks, as follows: (1) Perform an inspection at the first disassembly of the 2nd stage fan rotor from the low-pressure (LP) compressor after accumulation of 3,000 cycles-in-service (CIS) since the last inspection of the blade root attachment, not to exceed 10,000 CIS since last inspection. (2) If the 2nd stage fan blades were new at their last installation onto the 2nd stage fan disk, inspect at the first disassembly of the 2nd stage fan rotor from the LP compressor after accumulating 3,000 cycles-since-new (CSN), not to exceed 10,000 CSN. (3) Thereafter, inspect the 2nd stage fan blades at each disassembly of the 2nd stage fan rotor from the LP compressor after accumulating 3,000 CIS, not to exceed 10,000 CIS since the last inspection. (4) Guidance on performing ECIs and UIs of the 2nd stage fan blade pin-root holes and blade root attachments can be found in Pratt & Whitney Maintenance Advisory Notice MAN–JT8D–1–08. (5) Remove from service before further flight any 2nd stage fan blades that are found cracked. Optional Terminating Action (g) For JT8D–9, –9A, –11, –15, and –17 engines, as optional terminating action to the repetitive inspections required by this AD, replace the affected 2nd stage fan blades with redesigned 2nd stage fan blades using Pratt & Whitney Service Bulletin No. 5866, Revision 2, dated October 20, 1998. VerDate Nov<24>2008 16:10 Aug 06, 2009 Jkt 217001 Alternative Methods of Compliance (h) The Manager, Engine Certification Office, FAA, 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 (i) Contact Kevin Dickert, Aerospace Engineer, Engine Certification Office, FAA, Engine and Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; e-mail: kevin.dickert@faa.gov; telephone (781) 238–7117, fax (781) 238– 7199, for more information about this AD. (j) Contact Pratt & Whitney, 400 Main St., East Hartford, CT 06108; telephone (860) 565–8770; fax (860) 565–4503, for a copy of the service information referenced in this AD. Issued in Burlington, Massachusetts, on August 3, 2009. Francis A. Favara, Manager, Engine and Propeller Directorate, Aircraft Certification Service. [FR Doc. E9–18941 Filed 8–6–09; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF HOMELAND SECURITY Coast Guard [Docket No. USCG–2009–0277] RIN 1625–AA00 Safety Zone; San Clemente Island, CA Coast Guard, DHS. Notice of proposed rulemaking. AGENCY: SUMMARY: The Coast Guard proposes establishing a safety zone around San Clemente Island in support of potentially hazardous military training and testing exercises. The existing zones do not sufficiently overlap potential danger zones and testing areas used by the Navy during live-fire and ocean research operations resulting in a delay or cancellation of these operations. The proposed safety zone would protect the public from hazardous, live-fire and testing operations and ensure operations proceed as scheduled. DATES: Comments and related material must be received by the Coast Guard on or before November 5, 2009. Requests for public meetings must be received by the Coast Guard on or before August 28, 2009. ADDRESSES: You may submit comments identified by docket number USCG– 2009–0277 using any one of the following methods: (1) Federal eRulemaking Portal: https://www.regulations.gov. PO 00000 Frm 00020 Fmt 4702 FOR FURTHER INFORMATION CONTACT: If you have questions on this proposed rule, call or e-mail Petty Officer Kristen Beer, Waterways Management, U.S. Coast Guard Sector San Diego, Coast Guard; telephone 619–278–7262, e-mail Kristen.A.Beer@uscg.mil. If you have questions on viewing or submitting material to the docket, call Renee V. Wright, Program Manager, Docket Operations, telephone 202–366–9826. SUPPLEMENTARY INFORMATION: Public Participation and Request for Comments 33 CFR Part 165 ACTION: (2) Fax: 202–493–2251. (3) Mail: Docket Management Facility (M–30), U.S. Department of Transportation, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC 20590– 0001. (4) Hand delivery: Same as mail address above, between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The telephone number is 202–366–9329. To avoid duplication, please use only one of these four methods. See the ‘‘Public Participation and Request for Comments’’ portion of the SUPPLEMENTARY INFORMATION section below for instructions on submitting comments. Sfmt 4702 We encourage you to participate in this rulemaking by submitting comments and related materials. All comments received will be posted without change to https:// www.regulations.gov and will include any personal information you have provided. Submitting Comments If you submit a comment, please include the docket number for this rulemaking (USCG–2009–0277), indicate the specific section of this document to which each comment applies, and provide a reason for each suggestion or recommendation. You may submit your comments and material online (via https:// www.regulations.gov) or by fax, mail, or hand deliver, but please use only one of these means. If you submit a comment online via https://www.regulations.gov, it will be considered received by the Coast Guard when you successfully transmit the comment. If you fax, hand deliver, or mail your comment, it will be considered as having been received by the Coast Guard when it is received at the Docket Management Facility. We recommend that you include your name and a mailing address, an e-mail address, or a telephone number in the body of your document so that we can E:\FR\FM\07AUP1.SGM 07AUP1

Agencies

[Federal Register Volume 74, Number 151 (Friday, August 7, 2009)]
[Proposed Rules]
[Pages 39582-39584]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: E9-18941]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2009-0317; Directorate Identifier 79-ANE-18]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: The FAA proposes to supersede an existing airworthiness 
directive (AD) for Pratt & Whitney JT8D-1, -1A, -1B, -7, -7A, -7B, -9, 
-9A, -11, -15, and -17 turbofan engines with 2nd stage fan blades, part 
number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402 
installed. That AD currently requires initial and repetitive ultrasonic 
inspection (UI) and fluorescent penetrant inspection (FPI) of those P/N 
2nd stage fan blades. This proposed AD would replace the required FPI 
with eddy current inspection (ECI) on all affected 2nd stage fan blades 
and would maintain the requirement of ultrasonic inspection (UI) of the 
blade root attachment on some of the affected 2nd stage fan blades. 
This proposed AD would also introduce an optional terminating action to 
the repetitive blade inspections for certain engine models. This 
proposed AD results from reports of 10 fractures of 2nd stage fan 
blades since AD 87-14-01R1 became effective. We are proposing this AD 
to prevent uncontained failure of 2nd stage fan blades, which could 
result in damage to the airplane.

DATES: We must receive any comments on this proposed AD by October 6, 
2009.

ADDRESSES: Use one of the following addresses to comment on this 
proposed 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.

[[Page 39583]]


FOR FURTHER INFORMATION CONTACT: Kevin Dickert, Aerospace Engineer, 
Engine Certification Office, FAA, Engine and Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments regarding this proposal. Send your comments to an address 
listed under ADDRESSES. Include ``Docket No. FAA-2009-0317; Directorate 
Identifier 79-ANE-18'' in the subject line of your comments. We 
specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of the proposed AD. We will consider 
all comments received by the closing date and may amend the proposed AD 
in light of those comments.
    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 proposed 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 proposed 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.

Discussion

    The FAA proposes to amend 14 CFR part 39 by superseding AD 87-14-01 
R1, Amendment 39-6359 (54 FR 43954, October 30, 1989). That AD requires 
initial and repetitive UI and FPI of P/N 433802, 645902, 759902, 
695932, 678102, and 746402 2nd stage fan blades. That AD was the result 
of reports of on-going fractures of 2nd stage fan blades since 1980. 
That condition, if not corrected, could result in uncontained failure 
of 2nd stage fan blades, which could result in damage to the airplane.

Actions Since AD 87-14-01 R1 Was Issued

    Since AD 87-14-01 R1 was issued, Pratt & Whitney has developed and 
published an ECI procedure for inspecting the 2nd stage fan blade pin-
root holes. We have reviewed this procedure and determined that 
mandating this ECI procedure will result in an increased level of 
safety for the affected engines.

FAA's Determination and Requirements of the Proposed AD

    We have evaluated all pertinent information and identified an 
unsafe condition that is likely to exist or develop on other products 
of this same type design. For that reason, we are proposing this AD, 
which would require, for 2nd stage fan blades P/Ns 678102 and 746402, 
an ECI of the blade pin-root holes for cracks, and for 2nd stage fan 
blades P/Ns 433802, 645902, 759902, and 695932, an ECI of the blade 
pin-root holes and UI the blade root attachment for cracks. This 
proposed AD would also eliminate the JT8D-1, -1A, and -1B engines from 
the applicability, because those engine models have either been 
converted to other affected engine models included in the proposed AD 
or retired from service.

Costs of Compliance

    We estimate that this proposed AD would affect 1,380 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 25 work-hours per engine to perform one inspection cycle, 
and that the average labor rate is $80 per work-hour. Based on these 
figures, we estimate the total cost of the proposed AD to U.S. 
operators to be $2,760,000.

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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 the proposed 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. Would 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD. See the ADDRESSES section for a location 
to examine the regulatory evaluation.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Safety.

The Proposed Amendment

    Under the authority delegated to me by the Administrator, the 
Federal Aviation Administration proposes to amend 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.


Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-6359 (54 FR 
43954, October 30, 1989) and by adding a new airworthiness directive to 
read as follows:

Pratt & Whitney: Docket No. FAA-2009-0317; Directorate Identifier 
79-ANE-18.

Comments Due Date

    (a) The Federal Aviation Administration (FAA) must receive 
comments on this

[[Page 39584]]

airworthiness directive (AD) action by October 6, 2009.

Affected ADs

    (b) This AD supersedes AD 87-14-01 R1, Amendment 39-6359.

Applicability

    (c) This AD applies to Pratt & Whitney JT8D-7, -7A, -7B, -9, -
9A, -11, -15, and -17 turbofan engines, with 2nd stage fan blades, 
part number (P/N) 433802, 645902, 759902, 695932, 678102, or 746402, 
installed. These engines are installed on, but not limited to, 
Boeing 727, 737, and McDonnell Douglas DC-9 series airplanes.

Unsafe Condition

    (d) This AD results from reports of 10 fractures of 2nd stage 
fan blades since AD 87-14-01R1 became effective. We are issuing this 
AD to prevent uncontained failure of 2nd stage fan blades, which 
could result in 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.

2nd Stage Fan Blade Inspections

    (f) For 2nd stage fan blades, P/N 678102 and P/N 746402, perform 
an eddy current inspection (ECI) of the blade pin-root holes for 
cracks, and for 2nd stage fan blades, P/Ns 433802, 645902, 759902, 
and 695932, perform an ECI of the blade pin-root holes and perform 
an ultrasonic inspection (UI) of the blade root attachment for 
cracks, as follows:
    (1) Perform an inspection at the first disassembly of the 2nd 
stage fan rotor from the low-pressure (LP) compressor after 
accumulation of 3,000 cycles-in-service (CIS) since the last 
inspection of the blade root attachment, not to exceed 10,000 CIS 
since last inspection.
    (2) If the 2nd stage fan blades were new at their last 
installation onto the 2nd stage fan disk, inspect at the first 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 cycles-since-new (CSN), not to exceed 10,000 CSN.
    (3) Thereafter, inspect the 2nd stage fan blades at each 
disassembly of the 2nd stage fan rotor from the LP compressor after 
accumulating 3,000 CIS, not to exceed 10,000 CIS since the last 
inspection.
    (4) Guidance on performing ECIs and UIs of the 2nd stage fan 
blade pin-root holes and blade root attachments can be found in 
Pratt & Whitney Maintenance Advisory Notice MAN-JT8D-1-08.
    (5) Remove from service before further flight any 2nd stage fan 
blades that are found cracked.

Optional Terminating Action

    (g) For JT8D-9, -9A, -11, -15, and -17 engines, as optional 
terminating action to the repetitive inspections required by this 
AD, replace the affected 2nd stage fan blades with redesigned 2nd 
stage fan blades using Pratt & Whitney Service Bulletin No. 5866, 
Revision 2, dated October 20, 1998.

Alternative Methods of Compliance

    (h) The Manager, Engine Certification Office, FAA, 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

    (i) Contact Kevin Dickert, Aerospace Engineer, Engine 
Certification Office, FAA, Engine and Propeller Directorate, 12 New 
England Executive Park, Burlington, MA 01803; e-mail: 
kevin.dickert@faa.gov; telephone (781) 238-7117, fax (781) 238-7199, 
for more information about this AD.
    (j) Contact Pratt & Whitney, 400 Main St., East Hartford, CT 
06108; telephone (860) 565-8770; fax (860) 565-4503, for a copy of 
the service information referenced in this AD.

    Issued in Burlington, Massachusetts, on August 3, 2009.
Francis A. Favara,
Manager, Engine and Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. E9-18941 Filed 8-6-09; 8:45 am]
BILLING CODE 4910-13-P
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