44052 Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules 

this inspection at intervals not to exceed 25 

hours TIS. 

(3) If there is no corrosion, leaking grease, 

condensation, or water, repeat this inspection 

at intervals not to exceed 100 hours TIS. 

(4) If there is corrosion, leaking grease, or 

water, deactivate the air conditioning system 

in accordance with the Accomplishment 

Instructions, Section 3.B.3, Paragraphs (a) 

through (ai) of Eurocopter Emergency Alert 

Service Bulletin No. EC 135–21A–013, dated 

June 6, 2011. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: Matt Wilbanks, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

matt.wilbanks@faa.gov. 

(2) For operations conducted under a 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. 

(g) Additional Information 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) AD 

No. 2011–0111R1, dated September 22, 2011. 

You may view a copy of the EASA AD in the 

AD Docket on the Internet at http:// 

www.regulations.gov. 

(h) Subject 

Joint Aircraft Service Component (JASC) 

Code: 2100, air conditioning system. 

Issued in Fort Worth, Texas, on July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–17632 Filed 7–22–13; 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] 

RIN 2120–AA64 

Airworthiness Directives; Sikorsky 

Aircraft Corporation (Sikorsky) Model 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Supplemental notice of 

proposed rulemaking (SNPRM); 

reopening of the comment period. 

SUMMARY: We are revising an earlier 

proposed airworthiness directive (AD) 

for the 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, which proposed 

establishing new fatigue life limits for 

certain GE engine gas generator turbine 

(GGT) rotor parts. The proposed AD was 

prompted by a reevaluation of the 

method for determining the life limit for 

certain GE engine gas generator turbine 

(GGT) rotor parts and the determination 

that these life limits need to be based on 

low cycle fatigue (LCF) events instead of 

hours time-in-service. This action 

would retain the previously proposed 

requirements but correct the life limit 

formula for a certain GGT rotor part. 

The proposed actions are intended to 

prevent fatigue failure of a GGT rotor 

part, engine failure, and subsequent loss 

of control of the helicopter. 

DATES: We must receive comments on 

this proposed AD by September 23, 

2013. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Docket: Go to 

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

online instructions for sending your 

comments electronically. 

• Fax: 202–493–2251. 

• Mail: Send comments to the U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue SE., Washington, 

DC 20590–0001. 

• Hand Delivery: Deliver to the 

‘‘Mail’’ address between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

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 

economic evaluation, any comments 

received and other information. The 

street address for the Docket Operations 

Office (telephone 800–647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

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: 

Comments Invited 

We invite you to participate in this 

rulemaking by submitting written 

comments, data, or views. We also 

invite comments relating to the 

economic, environmental, energy, or 

federalism impacts that might result 

from adopting the proposals in this 

document. The most helpful comments 

reference a specific portion of the 

proposal, explain the reason for any 

recommended change, and include 

supporting data. To ensure the docket 

does not contain duplicate comments, 

commenters should send only one copy 

of written comments, or if comments are 

filed electronically, commenters should 

submit only one time. 

We will file in the docket all 

comments that we receive, as well as a 

report summarizing each substantive 

public contact with FAA personnel 

concerning this proposed rulemaking. 

Before acting on this proposal, we will 

consider all comments we receive on or 

before the closing date for comments. 

We will consider comments filed after 

the comment period has closed if it is 

possible to do so without incurring 

expense or delay. We may change this 

proposal in light of the comments we 

receive. 

Discussion 

On August 30, 2012, we issued a 

notice of proposed rulemaking (NPRM) 

(77 FR 55166, September 7, 2012) for 

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 to require establishing a new 

life limit for certain GGT rotor parts 

based upon the accumulated LCF events 

of the GGT rotor parts. 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 time-in-service to LCF events. The 

GE T700–GE–701C engine is used in the 

military’s UH–60 fleet. Analysis and 

experience with this engine have caused 

the military to reduce the life limit of 

certain GGT rotor parts and to revise 

their maintenance documentation to 

reflect these revised life limits. The 

Sikorsky Model S–70 helicopters are 

similar to the military’s UH–60 fleet, 

some of which have been certificated by 

the FAA in the restricted category. The 

GE T700–GE–701C engine has not been 

type-certificated by the FAA for civil 

use, except to the extent that it is a part 

of a restricted category Model S–70 

helicopter. 


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Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules 44053 

Actions Since Previous NPRM Was 

Issued 

Since we issued the previous NPRM 

(77 FR 55166, September 7, 2012), we 

became aware that GE has issued T700 

Turboshaft Engine Service Bulletin 

(ESB) 72–0041, Revision 1, dated March 

12, 2010 (ESB 72–0041), to correct the 

formula under the ‘‘T700–GE–401C 

Stage 2 Disk PN 6064T12P01/P03 LCF 

Limit Diagram’’ in Figure 6. Other than 

this correction, the specifications in ESB 

72–0041 remain the same. 

This SNPRM proposes to retain the 

previously proposed requirements but 

apply the correct life limit formula 

depicted in Figure 6 of ESB 72–0041, 

Revision 1. Also, we are correcting a 

typographical error in the preamble of 

the previous NPRM in the ‘‘Related 

Service Information,’’ which referenced 

the ESB number as 72–041 rather than 

72–0041. As a result, we have 

determined that it is necessary to reopen 

the comment period to provide 

additional opportunity for the public to 

comment. 

Comments 

We gave the public the opportunity to 

comment on the original NPRM (77 FR 

55166, September 7, 2012), but we did 

not receive any comments. 

FAA’s Determination 

We are proposing this SNPRM 

because we evaluated all the relevant 

information and determined the unsafe 

condition described previously is likely 

to exist or develop in other products of 

these same type designs. 

Proposed Requirements of the SNPRM 

This SNPRM would retain the 

proposed requirements of the previous 

NPRM and would also propose inserting 

into the airworthiness limitations 

section of the maintenance manual or 

the instructions for continued 

airworthiness the figures contained in 

ESB No. T700 S/B 72–0041, Revision 1, 

dated March 12, 2010, instead of ESB 

No. T700 S/B 72–0041, dated October 1, 

2008. 

Costs of Compliance 

We estimate that this proposed AD 

would 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, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701: 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We 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 an economic 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. 

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): 

Sikorsky Aircraft Corporation: 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) Comments Due Date 

We must receive comments by September 

23, 2013. 

(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 (ESB) No. 

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 

ESB No. 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 ESB) 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: 


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44054 Federal Register / Vol. 78, No. 141 / Tuesday, July 23, 2013 / Proposed Rules 

1The effective date of the 2011 Wage Rule was 

previously revised to September 30, 2011, 76 FR 

45667 (Aug. 1, 2011); to November 30, 2011, 76 FR 

59896 (Sept. 28, 2011); to January 1, 2012, 76 FR 

73508 (Nov. 29, 2011); to October 1, 2012, 76 FR 

82115 (Dec. 30, 2011); to March 27, 2013, 77 FR 

60040 (Oct. 2, 2012); and to October 1, 2013, 78 FR 

19098 (Mar. 29, 2013). 

(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 ESB No. 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) Additional Information 

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. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 7250: Turbine Section. 

Issued in Fort Worth, Texas, on July 11, 

2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–17627 Filed 7–22–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF LABOR 

Employment and Training 

Administration 

20 CFR Part 655 

RIN 1205–AB61 

Wage Methodology for the Temporary 

Non-Agricultural Employment H–2B 

Program; Proposed Delay of Effective 

Date 

AGENCY: Employment and Training 

Administration, Labor. 

ACTION: Proposed delay of effective date; 

request for comments. 

SUMMARY: The Department of Labor 

(Department) is proposing to delay 

indefinitely the effective date of the 

Wage Methodology for the Temporary 

Non-agricultural Employment H–2B 

Program final rule (2011 Wage Rule), in 

order to comply with recurrent 

legislation that prohibits the Department 

from using any funds to implement it, 

and to permit time for consideration of 

public comments sought in conjunction 

with an interim final rule published 

April 24, 2013, 78 FR 24047. The 2011 

Wage Rule revised the methodology by 

which the Department calculates the 

prevailing wages to be paid to H–2B 

workers and United States workers 

recruited in connection with a 

temporary labor certification for use in 

petitioning the Department of Homeland 

Security to employ a nonimmigrant 

worker in H–2B status. The 2011 Wage 

Rule was originally scheduled to 

become effective on January 1, 2012, 

and the effective date has been extended 

a number of times, most recently to 

October 1, 2013.1 The Department is 

now proposing to delay the effective 

date of the 2011 Wage Rule until such 

time as Congress no longer prohibits the 

Department from implementing the 

2011 Wage Rule. 

DATES: Comments must be received on 

or before August 9, 2013. 

ADDRESSES: You may submit comments, 

identified by Regulatory Information 

Number (RIN) 1205–AB61, by any one 

of the following methods: 

Federal e-Rulemaking Portal: 

www.regulations.gov. Follow the Web 

site instructions for submitting 

comments. 

Mail or Hand Delivery/Courier: Please 

submit all written comments (including 

disk and CD–ROM submissions) to 

Michael Jones, Acting Administrator, 

Office of Policy Development and 

Research, Employment and Training 

Administration, U.S. Department of 

Labor, 200 Constitution Avenue NW., 

Room N–5641, Washington, DC 20210. 

Please submit your comments by only 

one method. Comments received by 

means other than those listed above or 

received after the comment period has 

closed will not be reviewed. The 

Department will post all comments 

received on http://www.regulations.gov 

without making any change to the 

comments, including any personal 

information provided. The http:// 

www.regulations.gov Web site is the 

Federal e-rulemaking portal and all 

comments posted there are available 

and accessible to the public. The 

Department caution commenters not to 

include personal information such as 

Social Security Numbers, personal 

addresses, telephone numbers, and 

email addresses in their comments as 

such information will become viewable 

by the public on the http:// 

www.regulations.gov Web site. It is the 

commenter’s responsibility to safeguard 

his or her information. Comments 

submitted through http:// 

www.regulations.gov will not include 

the commenter’s email address unless 

the commenter chooses to include that 

information as part of his or her 

comment. 

Postal delivery In Washington, DC, 

may be delayed due to security 

concerns. Therefore, the Department 

encourages the public to submit 

comments through the http:// 

www.regulations.gov Web site. 

Docket: For access to the docket to 

read background documents or 

comments received, go to the Federal 

eRulemaking portal at http:// 

www.regulations.gov. The Department 

will also make all the comments 

received available for public inspection 

during normal business hours at the 

Employment and Training 

Administration (ETA) Office of Policy 

Development and Research at the above 


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