77384 Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 

Special Attention Service Bulletin 747–53– 

2460, Revision 2, dated December 22, 2010. 

This parts installation prohibition ends the 

parts installation prohibition specified in 

paragraph (o) of AD 2008–18–07, 

Amendment 39–15664 (73 FR 56960, October 

1, 2008), for the airplanes identified in 

paragraph (c) of this AD. 

(m) Exceptions to Service Information 

Specifications 

Where Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010, specifies a post-repair 

detailed inspection in accordance with Table 

9, this AD requires a detailed inspection in 

accordance with paragraph 3.B., Part 2, of 

Boeing Special Attention Service Bulletin 

747–53–2460, Revision 2, dated December 

22, 2010. 

(n) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (o) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCREQUESTS@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(o) Related Information 

For more information about this AD, 

contact Bill Ashforth, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

phone: 425–917–6432; fax: 425–917–6590; 

email: bill.ashforth@faa.gov. 

(p) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(i) Boeing Special Attention Service 

Bulletin 747–53–2460, Revision 2, dated 

December 22, 2010. 

(ii) Reserved. 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

5) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on 

November 19, 2014. 

Suzanne Masterson, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2014–30132 Filed 12–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0072; Directorate 

Identifier 2013–NE–04–AD; Amendment 39– 

18017; AD 2014–23–01] 

RIN 2120–AA64 

Airworthiness Directives; Pratt & 

Whitney Division Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; correction. 

SUMMARY: The FAA is correcting an 

airworthiness directive (AD) that 

published in the Federal Register. That 

AD applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, 

PW4077, PW4077D, PW4084D, 

PW4090, and PW4090–3 turbofan 

engine models with certain second-stage 

high-pressure turbine (HPT) air seals 

installed. The time required to perform 

the initial eddy current inspection (ECI) 

in the Compliance section is incorrect. 

This document corrects that error. In all 

other respects, the original document 

remains the same. 

DATES: This final rule is effective on 

December 26, 2014. The effective date of 

AD 2014–23–01, Amendment 39–18017 

(79 FR 69369, November 21, 2014) 

remains December 26, 2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in this AD 

as of September 17, 2013 (78 FR 49111, 

August 13, 2013). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: JoAnn Theriault, Aerospace Engineer, 

Engine Certification Office, FAA, Engine 

& Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

phone: 781–238–7105; fax: 781–238– 

7199; email: jo-ann.theriault@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2014– 

23–01, Amendment 39–18017 (79 FR 

69369, November 21, 2014), requires 

initial and repetitive inspections for 

cracks in second-stage HPT air seals, the 

removal of the mating hardware if the 

second-stage HPT air seal is found with 

a through-crack, and a mandatory 

terminating action for all PW PW4074, 

PW4074D, PW4077, PW4077D, 

PW4084D, PW4090, and PW4090–3 

turbofan engine models with certain 

second-stage HPT air seals installed. 

As published, the time required to 

perform the initial ECI in the 

Compliance section is incorrect. AD 

2014–23–01, paragraph (e)(2)(i), requires 

an initial ECI for cracks within 1,000 

cycles-in-service after September 17, 

2013, or before further flight, whichever 

occurs later. That compliance time is 

more restrictive than intended and will 

likely ground airplanes. The intent was 

to require an initial ECI for cracks before 

reaching 2,200 cycles since new, or 

within 1,000 cycles-in-service after 

September 17, 2013, or before further 

flight, whichever occurs later. 

No other part of the preamble or 

regulatory information has been 

changed. 

The effective date of AD 2014–23–01 

remains December 26, 2014. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2013–15–09, Amendment 39–17525 (78 

FR 49111, August 13, 2013), and adding 

the following new AD: 

2014–23–01 Pratt & Whitney Division: 

Amendment 39–18017; Docket No. 

FAA–2013–0072; Directorate Identifier 

2013–NE–04–AD. 

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Federal Register / Vol. 79, No. 247 / Wednesday, December 24, 2014 / Rules and Regulations 77385 

(a) Effective Date 

This AD is effective December 26, 2014. 

(b) Affected ADs 

This AD supersedes AD 2013–15–09, 

Amendment 39–17525 (78 FR 49111, August 

13, 2013). 

(c) Applicability 

This AD applies to all Pratt & Whitney 

Division (PW) PW4074, PW4074D, PW4077, 

PW4077D, PW4084D, PW4090, and PW4090– 

3 turbofan engine models with second-stage 

high-pressure turbine (HPT) air seal, part 

number (P/N) 54L041, 50L960, or 50L976, 

installed. 

(d) Unsafe Condition 

This AD was prompted by additional 

reports of cracking in the second-stage HPT 

air seal. We are issuing this AD to prevent 

failure of the second-stage HPT air seal, 

which could lead to uncontained engine 

failure and damage to the airplane. 

(e) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(1) At the next piece-part exposure after the 

effective date of this AD, do the following: 

(i) Remove from service second-stage HPT 

air seals, P/Ns 50L960, 50L976, and 54L041. 

(ii) Perform a fluorescent-penetrant 

inspection (FPI) of the second-stage HPT air 

seal, P/N 54L041, for a through-crack in the 

front forward fillet radius. 

(iii) If a through-crack in the front forward 

fillet radius is found, remove the first-stage 

HPT hub, second-stage HPT hub, and secondstage HPT blade retaining plate from service. 

Do not reinstall the first-stage HPT hub, 

second-stage HPT hub, or second-stage HPT 

blade retaining plate into any engine. 

(2) For engines with second-stage HPT air 

seals, P/N 54L041, installed, perform initial 

and repetitive inspections for cracks on-wing 

until the part is removed from the engine as 

follows: 

(i) Perform an initial eddy current 

inspection (ECI) for cracks before reaching 

2,200 cycles since new, within 1,000 cyclesin-service after September 17, 2013, or before 

further flight, whichever occurs later. 

(ii) Thereafter, repeat the ECI every 1,200 

cycles since last inspection, or fewer, 

depending on the results of the inspection. 

(iii) Use section 4.0 of the appendix of PW 

Alert Service Bulletin (ASB) No. PW4G–112– 

A72–330, Revision 2, dated July 11, 2013, to 

perform the inspection and use paragraph 8 

of the Accomplishment Instructions of PW 

ASB No. PW4G–112–A72–330, Revision 2, 

dated July 11, 2013, to disposition the results 

of the inspection. 

(f) Installation Prohibition 

(1) After the effective date of this AD, do 

not install any second-stage HPT air seal, P/ 

N 54L041, P/N 50L960, or P/N 50L976, into 

any engine. 

(2) After the effective date of this AD, do 

not install any spare first-stage HPT hub, 

second-stage HPT hub, or second-stage HPT 

blade retaining plate that was previously 

mated in service to a second-stage HPT air 

seal, P/N 54L041, that was found to have a 

through-crack in the front forward fillet 

radius, into any engine. 

(g) Definitions 

For the purpose of this AD: 

(1) Piece-part exposure is when the secondstage HPT air seal is removed from the engine 

and fully disassembled. 

(2) A through-crack is a crack that has 

propagated through the thickness of the part 

and can be seen on both the inner diameter 

and outer diameter of the front forward fillet 

radius. 

(h) Credit for Previous Actions 

(1) If you performed an ECI of the secondstage HPT air seal before the effective date of 

this AD, using PW ASB No. PW4G–112– 

A72–330, Revision 1, dated February 14, 

2013, or an earlier version, you have met the 

requirements of paragraph (e)(2)(i) of this AD. 

(2) If you performed an in-shop FPI of the 

second-stage HPT air seal before the effective 

date of this AD, you have met the 

requirements of paragraph (e)(2)(i) of this AD. 

(i) 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. You may email your 

request to: ANE-AD-AMOC@faa.gov. 

(j) Related Information 

(1) For more information about this AD, 

contact Jo-Ann Theriault, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; phone: 781–238–7105; fax: 781–238– 

7199; email: jo-ann.theriault@faa.gov. 

(2) PW Service Bulletin (SB) No. PW4G– 

112–72–332, Revision 3, dated June 25, 2014, 

which is not incorporated by reference in this 

AD, can be obtained from PW, using the 

contact information in paragraph (k)(3) of 

this AD. This SB provides guidance on how 

to replace the second-stage HPT air seal with 

an air seal that is more resistant to low cycle 

fatigue cracks. 

(k) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless the AD specifies otherwise. 

(3) The following service information was 

approved for IBR on September 17, 2013 (78 

FR 49111, August 13, 2013). 

(i) Pratt & Whitney (PW) Alert Service 

Bulletin No. PW4G–112–A72–330, Revision 

2, dated July 11, 2013. 

(ii) Reserved. 

(4) For PW service information identified 

in this AD, contact Pratt & Whitney Division, 

400 Main St., East Hartford, CT 06108; 

phone: 860–565–8770; fax: 860–565–4503. 

(5) You may view this service information 

at 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. 

(6) You may view this service information 

at the National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

December 22, 2014. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine and 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2014–30283 Filed 12–23–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF HEALTH AND 

HUMAN SERVICES 

Food and Drug Administration 

21 CFR Part 172 

[Docket No. FDA–2009–F–0303] 

Food Additives Permitted for Direct 

Addition to Food for Human 

Consumption; Advantame 

AGENCY: Food and Drug Administration, 

HHS. 

ACTION: Final rule; response to 

objections. 

SUMMARY: The Food and Drug 

Administration (FDA or we) is 

responding to objections we received on 

the final rule that amended the food 

additive regulations to provide for the 

safe use of advantame as a non-nutritive 

sweetener and flavor enhancer in foods 

generally, except in meat and poultry. 

After reviewing the objections to the 

final rule, we have concluded that they 

do not provide a basis for modifying or 

revoking the regulation. We are also 

confirming the effective date of May 21, 

2014, for the final rule. 

DATES: The effective date of the final 

rule published on May 21, 2014 (79 FR 

29078), is confirmed: May 21, 2014. 

FOR FURTHER INFORMATION CONTACT: 

Felicia M. Ellison, Center for Food 

Safety and Applied Nutrition (HFS– 

265), Food and Drug Administration, 

5100 Paint Branch Pkwy., College Park, 

MD 20740–3835, 240–402–1264. 

SUPPLEMENTARY INFORMATION: 

I. Background 

In the Federal Register of July 21, 

2009 (74 FR 35871), we announced that 

a food additive petition (FAP 9A4778), 

had been filed by Ajinomoto Co., Inc., 

c/o Ajinomoto Corporate Services LLC, 

1120 Connecticut Ave. NW., suite 1010, 

Washington, DC 20036. The petition 

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