Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 549 

(n) 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 737–30–1058, Revision 4, dated 

November 3, 2011. 

(ii) Boeing Special Attention Service 

Bulletin 737–30–1058, Revision 5, dated 

April 24, 2013. 

(3) For Boeing 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 

December 20, 2013. 

Jeffrey E. Duven, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31307 Filed 1–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0945; Directorate 

Identifier 2010–SW–110–AD; Amendment 

39–17722; AD 2013–26–13] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Sikorsky Model S–70, S–70A, S–70C, S– 

70C (M), and S–70C (M1) helicopters 

with General Electric (GE) T700–GE– 

401C or T700–GE–701C engines 

installed. This AD requires establishing 

new fatigue life limits for certain GE 

engine gas generator turbine (GGT) rotor 

parts. This AD was prompted by a 

reevaluation of the method for 

determining the life limit for certain GE 

engine GGT rotor parts and the 

determination that these life limits 

should be based on low cycle fatigue 

(LCF) events instead of hours time-inservice (TIS). The actions are intended 

to prevent fatigue failure of a GGT rotor 

part, engine failure, and subsequent loss 

of control of the helicopter. 

DATES: This AD is effective February 10, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain documents listed in this AD 

as of February 10, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Attn: Manager, 

Commercial Technical Support, 

mailstop s581a, 6900 Main Street, 

Stratford, CT, telephone (800) 562–4409, 

email address tsslibrary@sikorsky.com, 

or at http://www.sikorsky.com. You may 

review a copy of the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth Texas 76137. 

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 AD, any 

incorporated-by-reference service 

information, the economic evaluation, 

any comments received, and other 

information. The street address for the 

Docket Operations Office (phone: 800– 

647–5527) is U.S. Department of 

Transportation, Docket Operations 

Office, M–30, West Building Ground 

Floor, Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Michael Davison, Flight Test Engineer, 

New England Regional Office, FAA, 12 

New England Executive Park, 

Burlington, MA 01803; phone: (781) 

238–7156; fax: (781) 238–7170; email: 

michael.davison@faa.gov. 

SUPPLEMENTARY INFORMATION:

Discussion 

On September 7, 2012, at 77 FR 

55166, the Federal Register published 

our notice of proposed rulemaking 

(NPRM), which proposed to amend 14 

CFR part 39 by adding an AD that 

would apply to Sikorsky Model S–70, 

S–70A, S–70C, S–70C (M), and S–70C 

(M1) helicopters with GE T700–GE– 

401C or T700–GE–701C engines 

installed. The NPRM proposed 

establishing new fatigue life limits for 

certain GE engine GGT rotor parts, 

based upon a formula in GE’s service 

information. The NPRM was prompted 

by the determination that the affected 

engines could fail due to fatigue unless 

the life limits of certain GE engine rotor 

parts are changed from hours TIS to LCF 

events. 

On July 23, 2013, at 78 FR 44052, the 

Federal Register published our 

supplemental notice of proposed 

rulemaking (SNPRM), which proposed 

to revise the formula in the NPRM for 

establishing the new fatigue life limits 

by using the correct formula in a newer 

revision of GE’s service information. 

Also, the SNPRM corrected a 

typographical error made in the 

preamble of the previous NPRM in the 

‘‘Related Service Information,’’ which 

referenced the service bulletin number 

as 72–041 rather than the correct service 

bulletin number 72–0041. 

The proposed actions in the SNPRM 

were intended to prevent failure of a 

GGT rotor part, engine failure, and 

subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

comment on the NPRM (77 FR 55166, 

September 7, 2012), and the SNPRM (78 

FR 44052, July 23, 2013), but we did not 

receive any comments. 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 

unsafe condition exists and is likely to 

exist or develop on other products of 

these same type designs and that air 

safety and the public interest require 

adopting the AD requirements as 

proposed in the SNPRM (78 FR 44052, 

July 23, 2013). 

Costs of Compliance 

We estimate that this AD will affect 9 

helicopters of U.S. registry. We estimate 

that operators may incur the following 

costs in order to comply with this AD: 

A minimal amount for work hours and 

labor costs because these parts are 

replaced as part of the periodic 

maintenance on the helicopter; a 

minimal amount of time to calculate the 

new retirement life; $360,000 to replace 

the GGT rotor parts per helicopter; and 

$3,240,000 to replace the GGT rotor 

parts for the entire U.S. operator fleet. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 


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550 Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 

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 

This AD will not have federalism 

implications under Executive Order 

13132. This AD will not have a 

substantial direct effect on the States, on 

the relationship between the national 

government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

(2) Is not a ‘‘significant rule’’ under 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

(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 an economic evaluation 

of the estimated costs to comply with 

this 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. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

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

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2013–26–13 Sikorsky Aircraft Corporation: 

Amendment 39–17722; Docket No. 

FAA–2012–0945; Directorate Identifier 

2010–SW–110–AD. 

(a) Applicability 

This AD applies to Model S–70, S–70A, S– 

70C, S–70C (M), and S–70C (M1) helicopters 

with General Electric (GE) T700–GE–401C or 

T700–GE–701C part-numbered engines, 

certificated in any category. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

critical engine part remaining in service 

beyond its fatigue life because the current life 

limit is based on hours time-in-service (TIS) 

instead of fatigue cycles. This condition 

could result in fatigue failure of an engine 

rotor part, engine failure, and subsequent loss 

of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 10, 

2014. 

(d) Compliance 

You are responsible for performing each 

action required by this AD within the 

specified compliance time unless it has 

already been accomplished prior to that time. 

(e) Required Actions 

(1) Before further flight, insert into the 

airworthiness limitations section of the 

maintenance manual or instructions for 

continued airworthiness the low cycle fatigue 

(LCF) limit diagrams shown in Figures 2 

through 7 (pages 9 through 14) of GE T700 

Turboshaft Engine Service Bulletin T700 S/ 

B 72–0041, Revision 1, dated March 12, 2010, 

for helicopters with the GE T700–GE–401C 

engine, or Figures 2 through 4 (pages 10 

through 12) of GE T700 Turboshaft Engine 

Service Bulletin T700 S/B 72–0038, dated 

October 1, 2008, for helicopters with the GE 

T700–GE–701C engine. The diagonal line on 

each diagram represents the new cycle life 

limit (a combination of full low cycle fatigue 

events (LCF1) and partial low cycle fatigue 

events (LCF2) as those terms are defined in 

the Accomplishment Instructions, paragraphs 

3.A.(1) and 3.A.(2) of each service bulletin) 

for each gas generator turbine (GGT) rotor 

part. A combination of LCF1 and LCF2, 

which results in a number below the 

diagonal line of the applicable diagram for 

each engine, indicates that the part has not 

reached its fatigue life limit. 

(2) Before further flight: 

(i) Obtain the actual LCF1 and LCF2 count 

from the engine ‘‘history recorder’’ (HR); 

(ii) Calculate the LCF1 and LCF2 fatigue 

retirement life for each GGT rotor part as 

follows: 

(A) Determine the actual LCF ratio by 

dividing the total actual LCF2 cycle count 

obtained from the HR by the total actual 

LCF1 cycle count obtained from the HR. Add 

to the actual counts from the HR any actual 

additional fatigue cycle incurred during any 

period in which the HR was inoperative. 

(B) Determine the LCF1 retirement life by 

dividing the maximum number of LCF2 

events obtained from the applicable diagram 

for each engine by the sum of the actual LCF 

ratio obtained by following paragraph 

(e)(2)(ii)(A) of this AD plus the quotient of 

the maximum number of LCF2 events from 

the applicable diagram for each engine 

divided by the maximum number of LCF1 

events from the applicable diagram for each 

engine. 

(C) Determine the LCF2 retirement life by 

multiplying the actual LCF ratio obtained by 

following paragraph (e)(2)(ii)(A) of this AD 

times the LCF1 retirement life determined by 

following paragraph (e)(2)(ii)(B) of this AD. 

(iii) Replace each GGT rotor part that has 

reached the new fatigue cycle life limit with 

an airworthy rotor part. 

(3) For helicopters with the GE T700–GE– 

401C engine, if you cannot determine the 

number of low cycle fatigue events manually 

from the HR or by combining both manual 

and HR counts, then the life limit for the 

GGT rotor part is the hours TIS for the part 

as shown in Table 1 of GE T700 Turboshaft 

Engine Service Bulletin T700 S/B 72–0041, 

dated August 21, 2009. 

(4) Before further flight, begin or continue 

to count the full and partial low fatigue cycle 

events and record on the component card or 

equivalent record that count at the end of 

each day for which the HR is inoperative. 

(f) Special Flight Permit 

Special flight permits will not be issued to 

allow flight in excess of life limits. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Michael Davison, Flight Test Engineer, New 

England Regional Office, FAA, 12 New 

England Executive Park, Burlington, MA 

01803; phone: (781) 238–7156; fax: (781) 

238–7170; email: michael.davison@faa.gov. 

(2) For operations conducted under 14 CFR 

part 119 operating certificate or under 14 

CFR part 91, subpart K, we suggest that you 

notify your principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office or certificate 

holding district office before operating any 

aircraft complying with this AD through an 

AMOC. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

(i) 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) General Electric (GE) T700 Turboshaft 

Engine Service Bulletin T700 S/B 72–0038, 

dated October 1, 2008. 

(ii) GE T700 Turboshaft Engine Service 

Bulletin T700 S/B 72–0041, dated August 21, 

2009. 


sroberts on DSK5SPTVN1PROD with RULES
Federal Register / Vol. 79, No. 3 / Monday, January 6, 2014 / Rules and Regulations 551 

(iii) GE T700 Turboshaft Engine Service 

Bulletin T700 S/B 72–0041, Revision 1, dated 

March 12, 2010. 

(3) For GE service information identified in 

this AD, contact Sikorsky Aircraft 

Corporation, Attn: Manager, Commercial 

Technical Support, mailstop s581a, 6900 

Main Street, Stratford, CT, telephone (800) 

562–4409, email address 

tsslibrary@sikorsky.com, or at http:// 

www.sikorsky.com. 

(4) You may view this service information 

at FAA, Office of the Regional Counsel, 

Southwest Region, 2601 Meacham Blvd., 

Room 663, Fort Worth, Texas 76137. For 

information on the availability of this 

material at the FAA, call (817) 222–5110. 

(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 Fort Worth, Texas, on December 

24, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31525 Filed 1–3–14; 8:45 am] 

BILLING CODE 4910–13–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R06–OAR–2006–0593; FRL–9905–07– 

Region–6] 

Approval and Promulgation of 

Implementation Plans; Texas; Control 

of Air Pollution by Permits for New 

Construction or Modification; Permits 

for Specific Designated Facilities 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Withdrawal of direct final rule. 

SUMMARY: On November 21, 2013, the 

Environmental Protection Agency (EPA) 

published a direct final rule approving 

portions of two revisions to the Texas 

State Implementation Plan (SIP) 

concerning the Permits for Specific 

Designated Facilities Program, also 

referred to as the FutureGen Program. 

The direct final action was published 

without prior proposal because EPA 

anticipated no adverse comments. EPA 

stated in the direct final rule that if we 

received relevant, adverse comments by 

December 23, 2013, EPA would publish 

a timely withdrawal in the Federal 

Register. EPA received a letter dated 

December 19, 2013, from the Texas 

Commission on Environmental Quality 

stating that the March 9, 2006, and July 

2, 2010, SIP revisions specific to the 

FutureGen program have been 

withdrawn from our consideration as 

revisions to the Texas SIP. Accordingly, 

EPA is withdrawing our direct final 

approval and in a separate rulemaking 

in today’s Federal Register we are also 

withdrawing the corresponding 

proposed approval. We find that no 

further action is necessary on the Texas 

FutureGen Program March 9, 2006 and 

July 2, 2010 SIP revisions. The State’s 

action also withdraws from EPA’s 

review the FutureGen Program 

component of the January 22, 2010 

Consent Decree between EPA and the 

BCCA Appeal Group, Texas Association 

of Business, and Texas Oil and Gas 

Association. This withdrawal is being 

taken under section 110 and parts C and 

D of the Federal Clean Air Act. 

DATES: The direct final rule published 

on November 21, 2013 (78 FR 69773), is 

withdrawn effective January 6, 2014. 

FOR FURTHER INFORMATION CONTACT: Ms. 

Adina Wiley (6PD–R), Air Permits 

Section, Environmental Protection 

Agency, Region 6, 1445 Ross Avenue 

(6PD–R), Suite 1200, Dallas, TX 75202– 

2733. The telephone number is (214) 

665–2115. Ms. Wiley can also be 

reached via electronic mail at 

wiley.adina@epa.gov. 

List of Subjects in 40 CFR Part 52 

Environmental protection, Air 

pollution control, Incorporation by 

reference, Intergovernmental relations, 

Reporting and recordkeeping 

requirements. 

Dated: December 20, 2013. 

Samuel Coleman, 

Acting Regional Administrator, Region 6. 

Accordingly, the amendments to 40 

CFR 52.2270 published in the Federal 

Register on November 21, 2013 (78 FR 

69773), which were to become effective 

on January 21, 2014, are withdrawn. 

[FR Doc. 2013–31437 Filed 1–3–14; 8:45 am] 

BILLING CODE 6560–50–P 

ENVIRONMENTAL PROTECTION 

AGENCY 

40 CFR Part 52 

[EPA–R06–OAR–2010–0612; FRL–9904–03– 

Region–6] 

Approval and Promulgation of 

Implementation Plans; Texas; Public 

Participation for Air Quality Permit 

Applications 

AGENCY: Environmental Protection 

Agency (EPA). 

ACTION: Final rule. 

SUMMARY: The Environmental Protection 

Agency (EPA) is approving revisions to 

the Texas State Implementation Plan 

(SIP) that establish the public 

participation requirements for air 

quality permits. EPA finds that these 

revisions to the Texas SIP comply with 

the Federal Clean Air Act (the Act or 

CAA) and EPA regulations and are 

consistent with EPA policies. Texas 

submitted the public participation 

provisions in four separate revisions to 

the SIP on July 22, 1998; October 25, 

1999; July 2, 2010; and March 11, 2011. 

EPA is finalizing this action under 

section 110 and parts C and D of the 

Clean Air Act (the Act). 

DATES: This final rule will be effective 

on February 5, 2014. 

ADDRESSES: EPA has established a 

docket for this action under Docket ID 

No. EPA–R06–OAR–2010–0612. All 

documents in the docket are listed in 

the http://www.regulations.gov index. 

Although listed in the index, some 

information is not publicly available, 

e.g., Confidential Business Information 

or other information the disclosure of 

which is restricted by statute. Certain 

other material, such as copyrighted 

material, will be publicly available only 

in hard copy. Publicly available docket 

materials are available either 

electronically in http://

www.regulations.gov or in hard copy at 

the Air Permits Section (6PD–R), 

Environmental Protection Agency, 1445 

Ross Avenue, Suite 700, Dallas, Texas 

75202–2733. While all documents in the 

docket are listed in the index, some 

information may be publicly available 

only at the hard copy location (e.g., 

copyrighted material), and some may 

not be publicly available at either 

location (e.g., CBI). To inspect the hard 

copy materials, please schedule an 

appointment with the person listed in 

the FOR FURTHER INFORMATION CONTACT

paragraph below or Mr. Bill Deese at 

214–665–7253. 

FOR FURTHER INFORMATION CONTACT: Ms. 

Adina Wiley, Air Permits Section (6PD– 

R), Environmental Protection Agency, 

Region 6, 1445 Ross Avenue, Suite 700, 

Dallas, Texas 75202–2733, telephone 

214–665–2115; fax number 214–665– 

6762; email address wiley.adina@

epa.gov. 

SUPPLEMENTARY INFORMATION: 

Throughout this document whenever 

‘‘we,’’ ‘‘us,’’ or ‘‘our’’ is used, we mean 

EPA. 

Table of Contents 

I. Background for this Final Action 

II. Response to Comments 

III. Final Action 

IV. Statutory and Executive Order Reviews 


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