Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop Engines, 64421-64423 [2013-25460]

Download as PDF Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 64421 TABLE 1 TO PARAGRAPH (e)—DIFFUSER AND HPT CASE P/NS AND SERIAL NUMBERS—Continued Diffuser case part No. (P/N) Diffuser case S/N 1B7461 ........................................... 1B7461 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B4091–001 ................................... 1B4091–002 ................................... 1B4091–005 ................................... 1B7461 ........................................... 1B7477 ........................................... 1B7407 ........................................... 1B7407 ........................................... 1B7477 ........................................... 1B7477 ........................................... 1B7407–001 ................................... 1B7407 ........................................... DGGUAK1306 .............................. DGGUAK1356 .............................. DGGUAL1445 ............................... DGGUAL1492 ............................... DGGUAL1501 ............................... DGGUAL1597 ............................... RT6356 ......................................... ST2044 ......................................... PF3203 ......................................... DGGUAK1377 .............................. DGGUAL1548 ............................... DGGUAK0189 .............................. DGUSAA0443 ............................... DGGUAL1441 ............................... DGGUAL1560 ............................... DGUSAA0329 ............................... DGUSAA0334 ............................... (2) For all diffuser and HPT cases: (i) At the next piece part exposure and every piece part exposure thereafter, perform a high sensitivity fluorescent-penetrant inspection (FPI) of the entire diffuser case rear flange (M-flange) and bolt holes. (ii) At the next piece part exposure and every piece part exposure thereafter, perform a high sensitivity FPI of the entire HPT case forward flange (M-flange) and bolt holes. (f) Prohibition Statement After the effective date of this AD, do not install any engine with a diffuser or HPT case with serial number listed in Table 1 to paragraph (e) of this AD, onto any aircraft, that was not inspected per paragraph (e) of this AD. mstockstill on DSK4VPTVN1PROD with PROPOSALS (g) Credit for Previous Actions If you performed an eddy current inspection of the diffuser case and HPT case M-flange using paragraphs 3.G. through 3.L. in the ‘‘For Engines Installed on the Aircraft’’ section or paragraphs 3.B. through 3.G. in the ‘‘For Engines Removed from the Aircraft’’ section of the Accomplishment Instructions of PW SB PW2000 72–763, dated March 22, 2013, you met the requirements of paragraph (e)(1) of this AD. (h) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. HPT case P/N 1B2440 1B2440 1A9030 1A9030 1A9030 1A9030 1B2440 1A9030 1A9030 1B2440 1B2440 1B2440 1B2440 1B2440 1A9030 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 1B2440 Issued in Burlington, Massachusetts, on October 7, 2013. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–25459 Filed 10–28–13; 8:45 am] (i) Related Information (1) For more information about this AD, contact Robert Morlath, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England VerDate Mar<15>2010 16:26 Oct 28, 2013 Jkt 232001 ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... ......................................... Executive Park, Burlington, MA 01803; phone: 781–238–7154; fax: 781–238–7199; email: robert.c.morlath@faa.gov. (2) Pratt & Whitney Engine Manual, part number 1A6231, Chapter 72–41–00, Inspection/Check-02, (Task 72–41–00–230– 002) and Chapter 72–52–00, Inspection/ Check-02 (Task 72–52–00–230–000), which are not incorporated by reference in this AD, can be obtained from Pratt & Whitney, using the contact information in paragraph (i)(3) of this AD. (3) For service information identified in this AD, contact Pratt & Whitney, United Technologies Corporation, 400 Main St., East Hartford, CT 06108; phone: 860–565–8770; fax: 860–565–4503. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. BILLING CODE 4910–13–P PO 00000 Frm 00014 Fmt 4702 Sfmt 4702 HPT case S/N DKLBDB5153 DKLBDU3358 RM6353 PD3348 PD3280 ND5644 DKLBBP0225 DKLBBR3621 PD3290 WG6904 WV1807 WX2639 WZ4057 WX2664 RM6359 DKLBCM8956 DKLBCM0214 DKLBDB5069 DKLBB02548 DKLBDC7336 DKLBDU3372 WM6913 DKLBBF6606 DKLBBB2861 DKLBCT1660 DKLBB94641 DKLBBX8092 DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD] RIN 2120–AA64 Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for all Pratt & Whitney Canada Corp. (P&WC) PT6A– 114 and PT6A–114A turboprop engines. This proposed AD was prompted by several incidents of compressor turbine (CT) blade failure, including two fatalities, resulting in power loss and inflight shutdown (IFSD) of the engine. This proposed AD would require initial and repetitive borescope inspections (BSIs) of CT blades, and the removal from service of blades that fail inspection. We are proposing this AD to prevent failure of CT blades, which could lead to damage to the engine or to the airplane. DATES: We must receive comments on this proposed AD by December 30, 2013. SUMMARY: E:\FR\FM\29OCP1.SGM 29OCP1 64422 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules You may send comments by any of the following methods: • 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. For service information identified in this proposed AD, contact Pratt & Whitney Canada Corp., 1000 MarieVictorin, Longueuil, Quebec, Canada, J4G 1A1; phone: 800–268–8000; fax: 450–647–2888; Internet: www.pwc.ca. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. ADDRESSES: 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 mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: 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. FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7176; fax: 781–238– 7199; email: james.lawrence@faa.gov. SUPPLEMENTARY INFORMATION: mstockstill on DSK4VPTVN1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the VerDate Mar<15>2010 16:26 Oct 28, 2013 Jkt 232001 closing date and may amend this proposed AD based on 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). Discussion Transport Canada Civil Aviation, which is the aviation authority for Canada, has issued Canada AD CF– 2013–21, dated August 1, 2013, (referred to hereinafter as ‘‘the MCAI’’), to correct an unsafe condition for the specified products. The MCAI states: There have been a number of reported incidents where compressor turbine (CT) blade failures have caused power loss on PT6A–114 & PT6A–114A engines, resulting in in-flight shutdown (IFSD). Investigation by engine manufacturer Pratt & Whitney Canada (P&WC) has determined that when operated at high power and high temperature settings, the subject CT blades are prone to crack/ fracture as result of creep and/or sulfidation. You may obtain further information by examining the MCAI in the AD docket. We are proposing this AD to prevent failure of CT blades, which could lead to damage to the engine or to the airplane. FAA’s Determination and Requirements of This Proposed AD This product has been approved by the aviation authority of Canada and is approved for operation in the United States. Pursuant to our bilateral agreement with Canada, they have notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by Transport Canada Civil Aviation and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require initial and repetitive BSI of CT blades and the removal from service of blades that fail the inspection. Costs of Compliance We estimate that this proposed AD affects 300 engines installed on aircraft PO 00000 Frm 00015 Fmt 4702 Sfmt 4702 of U.S. registry. We also estimate that it would take about 4 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $102,000. 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 proposed 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 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 this proposed regulation: (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), (3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction, and (4) 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 regulatory evaluation of the estimated costs to comply with this proposed AD and placed it in the AD docket. List of Subjects in 14 CFR Part 39 Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. E:\FR\FM\29OCP1.SGM 29OCP1 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules The Proposed Amendment (g) Definition Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 14 CFR part 39 as follows: CT blades eligible for installation are: (1) New CT blades, other than those listed in paragraphs (g)(3) and (g)(4) of this AD; (2) CT blades, other than those listed in paragraphs (g)(3) and (g)(4) of this AD, that have met the inspection requirements of paragraphs (e)(1) and (e)(2) of this AD; (3) CT blade, P/N 3072791–01, and Disk Balance Assembly, P/N 3072801–01; and (4) CT blade, P/N 3072791–02, and Disk Balance Assembly, P/N 3072801–02. 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 2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): ■ Pratt & Whitney Canada Corp.: Docket No. FAA–2013–0766; Directorate Identifier 2013–NE–26–AD. (a) Comments Due Date We must receive comments by December 30, 2013. (b) Affected ADs None. (c) Applicability This AD applies to all Pratt & Whitney Canada Corp. (P&WC) PT6A–114 and PT6A– 114A turboprop engines. mstockstill on DSK4VPTVN1PROD with PROPOSALS (d) Reason This AD was prompted by several incidents of compressor turbine (CT) blade failure, including two fatalities, resulting in power loss and in-flight shutdown (IFSD) of the engine. We are issuing this AD to prevent failure of CT blades, which could lead to damage to the engine or to the airplane. (e) Actions and Compliance Comply with this AD within the compliance times specified, unless already done. (1) Within 150 operating hours after the effective date of this AD, perform a borescope inspection (BSI) of CT blades for engines with 500 or more hours time since new (TSN) that have not been previously inspected, or more than 500 flight hours time since last inspection (TSLI). (2) Thereafter, repeat the inspection in paragraph (e)(1) of this AD within every additional 500 flight hours TSLI. (3) During the next hot section inspection (HSI) after the effective date of this AD, replace the complete set of CT blades with blades eligible for installation. (4) If CT blades listed in paragraphs (g)(1) or (g)(2) of this AD, are installed to comply with paragraph (e)(3) of this AD, you must still comply with the 500-hour TSLI repetitive inspection requirement of paragraph (e)(2) of this AD. (f) Optional Terminating Action Replacing all CT blades with new CT blades, P/N 3072791–01, and Disk Balance Assembly, P/N 3072801–01; or with new CT blades, P/N 3072791–02, and Disk Balance Assembly, P/N 3072801–02; is terminating action for this AD. VerDate Mar<15>2010 16:26 Oct 28, 2013 FEDERAL TRADE COMMISSION (h) Credit for Previous Actions [Amended] Jkt 232001 If you performed P&WC Service Bulletin (SB) No. PT6A–72–1669, Revision 9, dated June 28, 2013, or earlier versions, you have met the initial inspection requirements of this AD. However, you must still comply with the 500-hour TSLI repetitive inspection requirement of paragraph (e)(2) of this AD. (i) Alternative Methods of Compliance (AMOCs) The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request. (j) Related Information (1) For more information about this AD, contact James Lawrence, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7176; fax: 781–238–7199; email: james.lawrence@faa.gov. (2) Refer to Transport Canada Civil Aviation AD CF–2013–21, dated August 1, 2013, for more information. You may examine the AD on the Internet at https:// www.regulations.gov by searching for and locating it in Docket No. FAA–2013–0766. (3) For guidance on the initial and repetitive BSIs mandated by this AD, refer to P&WC SB No. PT6A–72–1669 and P&WC SB No. PT6A–72–1727, which are not incorporated by reference in this AD. The SBs can be obtained from Pratt & Whitney Canada Corp. using the contact information in paragraph (j)(4) of this AD. (4) For service information identified in this AD, contact Pratt & Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, Canada, J4G 1A1; phone: 800–268– 8000; fax: 450–647–2888; Internet: www.pwc.ca. (5) You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. Issued in Burlington, Massachusetts, on October 7, 2013. Colleen M. D’Alessandro, Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2013–25460 Filed 10–28–13; 8:45 am] BILLING CODE 4910–13–P PO 00000 Frm 00016 64423 Fmt 4702 Sfmt 4702 16 CFR Part 312 RIN 3084–AB20 Children’s Online Privacy Protection Rule Applications for Approval of Proposed Parental Consent Methods by AssertID, Inc., Imperium LLC, and iVeriFly, Inc.; Application for Approval of Safe Harbor Program by kidSAFE Seal Program Federal Trade Commission (FTC or Commission). ACTION: Notice of extension of Commission determination and public comment deadlines. AGENCY: The FTC is extending the deadlines for Commission determination of applications for approval of proposed parental consent methods by AssertID, Inc. (‘‘AssertID’’), Imperium LLC (‘‘Imperium’’), and iVeriFly, Inc. (‘‘iVeriFly’’) pursuant to the Children’s Online Privacy Protection Rule. In addition, the FTC is extending the deadline for filing public comments concerning Imperium’s application for approval of a parental consent method and the proposed self-regulatory guidelines submitted by the kidSAFE Seal Program (‘‘kidSAFE’’), owned and operated by Samet Privacy, LLC, under the safe harbor provision of the Children’s Online Privacy Protection Rule. SUMMARY: Written comments must be received by November 4, 2013. ADDRESSES: Interested parties may file comments online or on paper, by following the instructions in the Request for Comment part of the SUPPLEMENTARY INFORMATION section below. For comments concerning Imperium, write ‘‘Imperium Application for Parental Consent Method, Project No. P–135419’’ on your comment and file your comment online at https:// ftcpublic.commentworks.com/ftc/ pmcoppaimperiumapp, by following the instructions on the web-based form. For comments concerning kidSAFE, write ‘‘kidSAFE Application for Safe Harbor, Project No. P–135418’’ on your comment, and file your comment online at https://ftcpublic.commentworks.com/ ftc/coppakidsafeapp, by following the instructions on the web-based form. If you prefer to file your comment on paper, mail or deliver your comment to the following address: Federal Trade Commission, Office of the Secretary, Room H–113 (Annex E), 600 Pennsylvania Avenue NW., Washington, DC 20580. DATES: E:\FR\FM\29OCP1.SGM 29OCP1

Agencies

[Federal Register Volume 78, Number 209 (Tuesday, October 29, 2013)]
[Proposed Rules]
[Pages 64421-64423]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-25460]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0766; Directorate Identifier 2013-NE-26-AD]
RIN 2120-AA64


Airworthiness Directives; Pratt & Whitney Canada Corp. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for all 
Pratt & Whitney Canada Corp. (P&WC) PT6A-114 and PT6A-114A turboprop 
engines. This proposed AD was prompted by several incidents of 
compressor turbine (CT) blade failure, including two fatalities, 
resulting in power loss and in-flight shutdown (IFSD) of the engine. 
This proposed AD would require initial and repetitive borescope 
inspections (BSIs) of CT blades, and the removal from service of blades 
that fail inspection. We are proposing this AD to prevent failure of CT 
blades, which could lead to damage to the engine or to the airplane.

DATES: We must receive comments on this proposed AD by December 30, 
2013.

[[Page 64422]]


ADDRESSES: You may send comments by any of the following methods:
     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.
    For service information identified in this proposed AD, contact 
Pratt & Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, 
Canada, J4G 1A1; phone: 800-268-8000; fax: 450-647-2888; Internet: 
www.pwc.ca. You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA. 
For information on the availability of this material at the FAA, call 
781-238-7125.

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 mandatory 
continuing airworthiness information (MCAI), the regulatory evaluation, 
any comments received, and other information. The street address for 
the Docket Operations office (phone: 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.

FOR FURTHER INFORMATION CONTACT: James Lawrence, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7176; 
fax: 781-238-7199; email: james.lawrence@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0766; 
Directorate Identifier 2013-NE-26-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this proposed AD. We 
will consider all comments received by the closing date and may amend 
this proposed AD based on 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).

Discussion

    Transport Canada Civil Aviation, which is the aviation authority 
for Canada, has issued Canada AD CF-2013-21, dated August 1, 2013, 
(referred to hereinafter as ``the MCAI''), to correct an unsafe 
condition for the specified products. The MCAI states:

    There have been a number of reported incidents where compressor 
turbine (CT) blade failures have caused power loss on PT6A-114 & 
PT6A-114A engines, resulting in in-flight shutdown (IFSD). 
Investigation by engine manufacturer Pratt & Whitney Canada (P&WC) 
has determined that when operated at high power and high temperature 
settings, the subject CT blades are prone to crack/fracture as 
result of creep and/or sulfidation.

You may obtain further information by examining the MCAI in the AD 
docket. We are proposing this AD to prevent failure of CT blades, which 
could lead to damage to the engine or to the airplane.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of Canada 
and is approved for operation in the United States. Pursuant to our 
bilateral agreement with Canada, they have notified us of the unsafe 
condition described in the MCAI and service information referenced 
above. We are proposing this AD because we evaluated all information 
provided by Transport Canada Civil Aviation and determined the unsafe 
condition exists and is likely to exist or develop on other products of 
the same type design. This proposed AD would require initial and 
repetitive BSI of CT blades and the removal from service of blades that 
fail the inspection.

Costs of Compliance

    We estimate that this proposed AD affects 300 engines installed on 
aircraft of U.S. registry. We also estimate that it would take about 4 
hours per engine to comply with this proposed AD. The average labor 
rate is $85 per hour. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $102,000.

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 proposed 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 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 this proposed 
regulation:
    (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),
    (3) Will not affect intrastate aviation in Alaska to the extent 
that it justifies making a regulatory distinction, and
    (4) 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 regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 64423]]

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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 adding the following new airworthiness 
directive (AD):

Pratt & Whitney Canada Corp.: Docket No. FAA-2013-0766; Directorate 
Identifier 2013-NE-26-AD.

(a) Comments Due Date

    We must receive comments by December 30, 2013.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all Pratt & Whitney Canada Corp. (P&WC) PT6A-
114 and PT6A-114A turboprop engines.

(d) Reason

    This AD was prompted by several incidents of compressor turbine 
(CT) blade failure, including two fatalities, resulting in power 
loss and in-flight shutdown (IFSD) of the engine. We are issuing 
this AD to prevent failure of CT blades, which could lead to damage 
to the engine or to the airplane.

(e) Actions and Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) Within 150 operating hours after the effective date of this 
AD, perform a borescope inspection (BSI) of CT blades for engines 
with 500 or more hours time since new (TSN) that have not been 
previously inspected, or more than 500 flight hours time since last 
inspection (TSLI).
    (2) Thereafter, repeat the inspection in paragraph (e)(1) of 
this AD within every additional 500 flight hours TSLI.
    (3) During the next hot section inspection (HSI) after the 
effective date of this AD, replace the complete set of CT blades 
with blades eligible for installation.
    (4) If CT blades listed in paragraphs (g)(1) or (g)(2) of this 
AD, are installed to comply with paragraph (e)(3) of this AD, you 
must still comply with the 500-hour TSLI repetitive inspection 
requirement of paragraph (e)(2) of this AD.

(f) Optional Terminating Action

    Replacing all CT blades with new CT blades, P/N 3072791-01, and 
Disk Balance Assembly, P/N 3072801-01; or with new CT blades, P/N 
3072791-02, and Disk Balance Assembly, P/N 3072801-02; is 
terminating action for this AD.

(g) Definition

    CT blades eligible for installation are:
    (1) New CT blades, other than those listed in paragraphs (g)(3) 
and (g)(4) of this AD;
    (2) CT blades, other than those listed in paragraphs (g)(3) and 
(g)(4) of this AD, that have met the inspection requirements of 
paragraphs (e)(1) and (e)(2) of this AD;
    (3) CT blade, P/N 3072791-01, and Disk Balance Assembly, P/N 
3072801-01; and
    (4) CT blade, P/N 3072791-02, and Disk Balance Assembly, P/N 
3072801-02.

(h) Credit for Previous Actions

    If you performed P&WC Service Bulletin (SB) No. PT6A-72-1669, 
Revision 9, dated June 28, 2013, or earlier versions, you have met 
the initial inspection requirements of this AD. However, you must 
still comply with the 500-hour TSLI repetitive inspection 
requirement of paragraph (e)(2) of this AD.

(i) Alternative Methods of Compliance (AMOCs)

    The Manager, Engine Certification Office, FAA, may approve AMOCs 
to this AD. Use the procedures found in 14 CFR 39.19 to make your 
request.

(j) Related Information

    (1) For more information about this AD, contact James Lawrence, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7176; fax: 781-238-7199; email: 
james.lawrence@faa.gov.
    (2) Refer to Transport Canada Civil Aviation AD CF-2013-21, 
dated August 1, 2013, for more information. You may examine the AD 
on the Internet at https://www.regulations.gov by searching for and 
locating it in Docket No. FAA-2013-0766.
    (3) For guidance on the initial and repetitive BSIs mandated by 
this AD, refer to P&WC SB No. PT6A-72-1669 and P&WC SB No. PT6A-72-
1727, which are not incorporated by reference in this AD. The SBs 
can be obtained from Pratt & Whitney Canada Corp. using the contact 
information in paragraph (j)(4) of this AD.
    (4) For service information identified in this AD, contact Pratt 
& Whitney Canada Corp., 1000 Marie-Victorin, Longueuil, Quebec, 
Canada, J4G 1A1; phone: 800-268-8000; fax: 450-647-2888; Internet: 
www.pwc.ca.
    (5) You may view this service information at the FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, 
MA. For information on the availability of this material at the FAA, 
call 781-238-7125.

    Issued in Burlington, Massachusetts, on October 7, 2013.
Colleen M. D'Alessandro,
Assistant Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2013-25460 Filed 10-28-13; 8:45 am]
BILLING CODE 4910-13-P

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