Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations 3303 

final rule because the Commission was 

not required to publish a notice of 

proposed rulemaking or to seek public 

comment under 5 U.S.C. 553 or any 

other laws. 5 U.S.C. 603(a), 604(a). 

Therefore, no regulatory flexibility 

analysis is required. 

List of Subjects in 11 CFR Part 111 

Administrative practice and 

procedure, Elections, Law enforcement, 

Penalties. 

For the reasons set out in the 

preamble, the Federal Election 

Commission amends Subchapter A of 

Chapter I of Title 11 of the Code of 

Federal Regulations as follows: 

PART 111—COMPLIANCE 

PROCEDURE (2 U.S.C. 437g, 437d(a)) 

■ 1. The authority citation for part 111 

continues to read as follows: 

Authority: 2 U.S.C. 432(i), 437g, 437d(a), 

438(a)(8); 28 U.S.C. 2461 nt; 31 U.S.C. 3701, 

3711, 3716–3719, and 3720A, as amended; 31 

CFR parts 285 and 900–904. 

■ 2. Revise § 111.30 to read as follows: 

§ 111.30 When will subpart B apply? 

Subpart B applies to violations of the 

reporting requirements of 2 U.S.C. 

434(a) committed by political 

committees and their treasurers that 

relate to the reporting periods that begin 

on or after July 14, 2000, and that end 

on or before the date specified by 2 

U.S.C. 437g(a)(4)(C)(v). This subpart, 

however, does not apply to reports that 

relate to reporting periods that end 

between January 1, 2014, and January 

21, 2014. 

§ 111.41 [Removed and Reserved] 

■ 3. Remove and reserve § 111.41. 

Dated: January 13, 2014. 

On behalf of the Commission. 

Lee E. Goodman, 

Chairman, Federal Election Commission. 

[FR Doc. 2014–00960 Filed 1–17–14; 8:45 am] 

BILLING CODE 6715–01–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0636; Directorate 

Identifier 2012–SW–065–AD; Amendment 

39–17709; AD 2013–25–13] 

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, and S– 

70C helicopters. This AD establishes a 

new life limit based on a prorated 

formula for certain identified 

components (parts) installed on Model 

S–70, S–70A, and S–70C helicopters 

after being previously installed on 

certain military model helicopters. This 

AD was prompted by the discovery that 

certain parts have been interchanged 

between military helicopter models 

with different life limits and the 

possibility that these same parts can be 

interchanged with civilian models with 

different life limits. The actions are 

intended to establish a pro-rated in 

service life limit for each identified part 

to prevent fatigue failure of a part and 

subsequent loss of control of the 

helicopter. 

DATES: This AD is effective February 25, 

2014. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of February 25, 2014. 

ADDRESSES: For service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Customer Service 

Engineering, 124 Quarry Road, 

Trumbull, CT 06611; telephone 1–800– 

Winged–S or 203–416–4299; email 

sikorskywcs@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, 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, 

Boston Aircraft Certification Office, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, 

Massachusetts 01803; telephone (781) 

238–7156; email michael.davison@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On July 23, 2013, at 78 FR 44045, 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, and S– 

70C helicopters. The NPRM proposed 

inserting the component life prorating 

formula into the airworthiness 

limitation section of the maintenance 

manual or instructions for continued 

airworthiness, calculating the new life 

limit for each part by applying the 

formula, and establishing life limits for 

certain parts without applying the 

formula. Furthermore, the NPRM 

proposed updating the component log 

or equivalent record with the new inservice life limit and replacing each part 

that has reached or exceeded its new life 

limit with an airworthy part. Lastly, the 

NPRM proposed prohibiting installation 

of any applicable part on a Model S–70, 

S–70A, or S–70C helicopter if the 

number of hours is unknown or if 

certain parts have been previously 

installed on a Model UH–60M 

helicopter. The NPRM was prompted by 

the discovery that certain parts with 

identical part numbers but different life 

limits have been interchanged between 

military helicopter models and the 

possibility that these same parts can be 

interchanged with civilian models with 

different life limits. 

The proposed requirements were 

intended to establish a pro-rated in 

service life limit for each identified part 

to prevent fatigue failure of a part and 

subsequent loss of control of the 

helicopter. 

Comments 

We gave the public the opportunity to 

participate in developing this AD, but 

we did not receive any comments on the 

NPRM (78 FR 44045, July 23, 2013). 

FAA’s Determination 

We have reviewed the relevant 

information and determined that an 


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3304 Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations 

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. 

Costs of Compliance 

We estimate that this AD affects 9 

helicopters of U.S. Registry. 

We estimate that the cost to insert 

pages into the aircraft’s airworthiness 

limitation section is negligible. 

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 

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. 

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): 

2013–25–13 Sikorsky Aircraft Corporation 

(Sikorsky): Amendment 39–17709; 

Docket No. FAA–2013–0636; Directorate 

Identifier 2012–SW–065–AD. 

(a) Applicability 

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

and S–70C helicopters, certificated in any 

category, with the following parts installed: 

(1) Spindle and liner assembly, part 

number (P/N) 38023–10374–041; 

(2) Main Rotor Hub, P/N 70070–10046–055 

and –056; 

(3) Main Rotor Spindle nut, P/N 70102– 

08105–102; 

(4) Main Rotor Control Horn, P/N 70102– 

08111–047; 

(5) Main Rotor Hub, P/N 70103–08112–041 

and –047; 

(6) Rotating Swashplate, P/N 70104– 

08001–044 and –045; 

(7) Main Rotor Shaft Extension, P/N 

70351–08186–043; 

(8) Main Rotor Gear Box Housing, P/N 

70351–38110–043, –044, and –045; 

(9) Main Rotor Shaft, P/N 70351–38131– 

042; 

(10) Output Bevel Gear and Shaft, P/N 

70358–06620–101 and –102; 

(11) Left Tie Rod Assembly, P/N 70400– 

08115–043, –045, –046, and –047; 

(12) Forward Bellcrank Support Assembly, 

P/N 70400–08162–042; 

(13) Lateral Servo Bellcrank, P/N 70400– 

08166–041; or 

(14) Tail Rotor Servo Assembly, P/N 

70410–06520–044 through –046. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

critical part remaining in service beyond its 

life limit due to previously being installed on 

a different helicopter model with higher 

usage and flight loads. This condition could 

result in fatigue failure of a critical part and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective February 25, 

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) Within 25 hours time-in-service (TIS): 

(i) Insert into the airworthiness limitation 

section of the maintenance manual or 

instructions for continued airworthiness the 

component life prorating formula in Section 

1.1.3, Component Life Prorating, pages 1–25 

and 1–26, of Sikorsky Technical Manual TM 

1–70–23AW–2, Change 3, dated April 15, 

2012. 

(ii) Using the service life limits in Table 1 

to Paragraph (e) of this AD, apply the 

component life prorating formula and 

calculate the new life limit for each specified 

part. If the number of hours of a part is 

unknown, that part cannot be installed on a 

Sikorsky Model S–70, S–70A, or S–70C 

helicopter. Do not calculate a new life limit 

for the part where the Model SH–60 life limit 

is higher than the life limit on Models S–70, 

S–70A, and S–70C. 

TABLE 1 TO PARAGRAPH (e) 

P/N Part description 

S–70, S–70A, 

S–70C service 

life 

UH–60M 

service life 

SH–60B/F 

service life 

38023–10374–041 .......................................... Spindle and Liner Assembly .......................... 8,000 6,400 10,000

70070–10046–055 and –056 .......................... Main Rotor Hub .............................................. 5,100 3,100 1N/A 

70102–08105–102 .......................................... Main Rotor Spindle Nut .................................. 8,000 6,400 10,000 

70102–08111–047 .......................................... Main Rotor Control Horn ................................ 20,000/1,300 2/ 

2,500 2

10,000 1 N/A 

70103–08112–041 and –047 .......................... Main Rotor Hub .............................................. 5,100 3,100 1 N/A 

70104–08001–044–045 .................................. Rotating Swashplate ...................................... 11,000 4,600 9,600 

70351–08186–043 .......................................... Main Rotor Shaft Extension ........................... 14,000 4,900 16,000 

70351–38110–043, –044, and –045 ............... Main Rotor Gear Box Housing ....................... 11,000 4,000 9,000 

70351–38131–042 .......................................... Main Rotor Shaft ............................................ 17,000 5,200 19,000 

70358–06620–101 and –102 .......................... Output Bevel Gear and Shaft ........................ 5,000 1,800 1 N/A 


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Federal Register / Vol. 79, No. 13 / Tuesday, January 21, 2014 / Rules and Regulations 3305 

TABLE 1 TO PARAGRAPH (e)—Continued 

P/N Part description 

S–70, S–70A, 

S–70C service 

life 

UH–60M 

service life 

SH–60B/F 

service life 

70400–08115–043, –045, –046, and –047 .... Left Tie Rod Assembly ................................... 14,000 4,600 6,300 

70400–08162–042 .......................................... Forward Bellcrank Support Assembly ............ 14,000/2,500 3 5,600 7,600 

70400–08166–041 .......................................... Lateral Servo Bellcrank .................................. 20,000 11,000 14,000 

70410–06520–044 through –046 .................... Tail Rotor Servo Assembly ............................ 15,000 11,000 1 N/A 

1There is no service life limit listed because the parts on Model SH–60B/F have a different P/N than the parts on Models S–70, S–70A, and 

S–70C. 2For serial number (S/N) 32479930 through 324791859, with CAGE code 60078, the life limit is 1,300 hours TIS. 

For S/N A241–07543 through A241–07594, A241–07706 through A241–07755, A241–07768 through A241–07771, A241–07800 through 

A241–07831, R241–00101 through R241–00355, R241–00701 through R241–00966, and R241–01001 through R241–01166, the life limit is 

2,500 hours TIS. 3For S/N A–367–00001 through A367–00035, with CAGE code 78286, the life limit is 2,500 hours TIS. 

(iii) Record the newly-established life limit 

of each part on the part’s component log card 

or equivalent record. 

(2) After establishing the new life limit, 

replace each part that has reached or 

exceeded its new life limit with an airworthy 

part before further flight. 

(3) Do not install the following parts on a 

Model S–70, S–70A, or S–70C helicopter if 

they have been previously installed on a 

Model UH–60M helicopter: 

(i) Bolt, self retaining, P/N 70103–08801– 

102; 

(ii) Bifilar, P/N 70107–08400–046; 

(iii) Aft Bellcrank, P/N 70400–08102–045; 

(iv) Aft Walking Beam Assembly, P/N 

70400–08104–048; or 

(v) Close Tolerance Bolt, P/N 70400– 

26802–102 and –103. 

(f) Alternative Methods of Compliance 

(AMOC) 

(1) The Manager, Boston Aircraft 

Certification Office, FAA, may approve 

AMOCs for this AD. Send your proposal to: 

Michael Davison, Flight Test Engineer, 

Boston Aircraft Certification Office, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, Massachusetts 

01803; telephone (781) 238–7156; email 

michael.davison@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) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6220 Main Rotor Hub, 6230 Main Rotor 

Mast/Swashplate, 6320 Main Rotor Gearbox, 

6310 Engine/Transmission Coupling, 6510 

Tail Rotor Drive Shaft. 

(h) 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) Pages 1–25 and 1–26, Section 1.1.3, 

Component Life Prorating, of Sikorsky 

Technical Manual TM 1–70–23AW–2, 

Change 3, dated April 15, 2012. 

(ii) Reserved. 

(3) For Sikorsky service information 

identified in this AD, contact Sikorsky 

Aircraft Corporation, Customer Service 

Engineering, 124 Quarry Road, Trumbull, CT 

06611; telephone 1–800–Winged–S or 203– 

416–4299; email sikorskywcs@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 

5, 2013. 

Kim Smith, 

Directorate Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2013–31459 Filed 1–17–14; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 71 

[Docket No. FAA–2012–0661; Airspace 

Docket No. 09–AWA–4] 

RIN 2120–AA66 

Amendment to Class B Airspace; 

Detroit, MI 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This action modifies the 

Detroit, MI, Class B airspace area to 

contain aircraft conducting published 

instrument procedures at Detroit 

Metropolitan Wayne County Airport 

(DTW), Detroit, MI, within Class B 

airspace. The FAA is taking this action 

to support containment of aircraft 

operations using the three existing dual 

Simultaneous Independent Instrument 

Landing System (SIILS) configurations, 

runways 22R/21L, runways 4L/3R and 

runways 27L/27R, as well as support 

containment of aircraft operations for 

triple SIILS operations to runways 4L/ 

4R/3R and runways 21L/22L/22R. This 

action will enhance safety, improve the 

flow of air traffic, and reduce the 

potential for midair collisions in the 

DTW terminal area, while 

accommodating the concerns of all 

airspace users. Furthermore, this effort 

supports the FAA’s national airspace 

redesign goal of optimizing terminal and 

enroute airspace areas to reduce aircraft 

delays and improve system capacity. 

DATES: Effective Date: 0901 UTC, April 

3, 2014. The Director of the Federal 

Register approves this incorporation by 

reference action under 3 CFR part 51, 

subject to the annual revision of FAA 

Order 7400.9 and publication of 

conforming amendments. 

FOR FURTHER INFORMATION CONTACT: 

Colby Abbott, Airspace Policy and 

Regulations Group, Office of Airspace 

Services, Federal Aviation 

Administration, 800 Independence 

Avenue SW., Washington, DC 20591; 

telephone: (202) 267–8783. 

SUPPLEMENTARY INFORMATION: 

History 

On August 14, 2012, the FAA 

published in the Federal Register a 

notice of proposed rulemaking (NPRM) 

to modify the Detroit Class B airspace 

area (77 FR 48476). This action 

proposed to expand the lateral and 

vertical limits of the Detroit Class B 

airspace area to provide additional 

airspace needed to contain dual SIILS 

procedures and associated traffic 

patterns supporting runways 22R/21L, 

runways 4L/3R, and runways 27L/27R 


tkelley on DSK3SPTVN1PROD with RULES