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 HPT case P/N HPT case S/N 

1B7461 ........................................... DGGUAK1306 .............................. 1B2440 ......................................... DKLBDB5153 

1B7461 ........................................... DGGUAK1356 .............................. 1B2440 ......................................... DKLBDU3358 

1B7477 ........................................... DGGUAL1445 ............................... 1A9030 ......................................... RM6353 

1B7477 ........................................... DGGUAL1492 ............................... 1A9030 ......................................... PD3348 

1B7477 ........................................... DGGUAL1501 ............................... 1A9030 ......................................... PD3280 

1B7477 ........................................... DGGUAL1597 ............................... 1A9030 ......................................... ND5644 

1B4091–001 ................................... RT6356 ......................................... 1B2440 ......................................... DKLBBP0225 

1B4091–002 ................................... ST2044 ......................................... 1A9030 ......................................... DKLBBR3621 

1B4091–005 ................................... PF3203 ......................................... 1A9030 ......................................... PD3290 

1B7461 ........................................... DGGUAK1377 .............................. 1B2440 ......................................... WG6904 

1B7477 ........................................... DGGUAL1548 ............................... 1B2440 ......................................... WV1807 

1B7407 ........................................... DGGUAK0189 .............................. 1B2440 ......................................... WX2639 

1B7407 ........................................... DGUSAA0443 ............................... 1B2440 ......................................... WZ4057 

1B7477 ........................................... DGGUAL1441 ............................... 1B2440 ......................................... WX2664 

1B7477 ........................................... DGGUAL1560 ............................... 1A9030 ......................................... RM6359 

1B7407–001 ................................... DGUSAA0329 ............................... 1B2440 ......................................... DKLBCM8956 

1B7407 ........................................... DGUSAA0334 ............................... 1B2440 ......................................... DKLBCM0214 

1B2440 ......................................... DKLBDB5069 

1B2440 ......................................... DKLBB02548 

1B2440 ......................................... DKLBDC7336 

1B2440 ......................................... DKLBDU3372 

1B2440 ......................................... WM6913 

1B2440 ......................................... DKLBBF6606 

1B2440 ......................................... DKLBBB2861 

1B2440 ......................................... DKLBCT1660 

1B2440 ......................................... DKLBB94641 

1B2440 ......................................... DKLBBX8092 

(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. 

(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. 

(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 

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. 

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] 

BILLING CODE 4910–13–P 

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 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. 

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64422 Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

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 http://

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. 

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Federal Register / Vol. 78, No. 209 / Tuesday, October 29, 2013 / Proposed Rules 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 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

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 http://

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 

FEDERAL TRADE COMMISSION 

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 

AGENCY: Federal Trade Commission 

(FTC or Commission). 

ACTION: Notice of extension of 

Commission determination and public 

comment deadlines. 

SUMMARY: 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. 

DATES: 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. 

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