63852 Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations 

(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): 

2013–20–51 Agusta S.p.A: Amendment 39– 

17628; Docket No. FAA–2013–0881; 

Directorate Identifier 2013–SW–056–AD. 

(a) Applicability 

This AD applies to the following Agusta 

S.p.A. (Type certificate currently held by 

AgustaWestland S.p.A) (Agusta) helicopters, 

with a tail rotor drive shaft flexible disc 

coupling (Thomas coupling) nut, part 

number (P/N) MS21042L4, certificated in any 

category: 

(i) Model A109A, A109A II, A109C, A109E, 

A109S, A109K2, AW109SP helicopters; and 

(ii) Model A119 and AW119 MKII 

helicopters. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

production deficiency in a certain Thomas 

coupling nut. This condition could result in 

failure of the Thomas coupling, failure of the 

tail drive shaft, and subsequent loss of 

control of the helicopter. 

(c) Effective Date 

This AD is effective October 25, 2013 to all 

persons except those persons to whom it was 

made immediately effective by Emergency 

AD 2013–20–51, issued on October 3, 2013, 

which contained the requirements of this 

amendment. 

(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, using a borescope 

or light source and mirror, inspect each 

Thomas coupling nut for a crack. If any 

Thomas coupling nut is cracked, before 

further flight, replace all the Thomas 

coupling nuts with nuts, P/N NAS1805–4, 

torqueing each nut to 5.6–7.9 Nm. 

(2) Within 10 hours time-in-service or 30 

days, whichever occurs first, replace each 

Thomas coupling nut, P/N MS21042L4, with 

a nut, P/N NAS1805–4, torqueing each nut to 

5.6–7.9 Nm. 

(3) After the effective date of this EAD, do 

not install a nut, P/N MS21042L4, on any 

Thomas coupling. 

(f) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to Gary Roach, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5110; email 

gary.b.roach@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 

(1) Agusta Alert Bollettino Tecnico (ABT) 

No. 109K–58, ABT No. 109–136, ABT No. 

109EP–130, ABT No. 109L–066, ABT No. 

109S–055, ABT No. 109SP–069, and ABT No. 

119–061, all dated September 20, 2013, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. For service information 

identified in this AD, contact: Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http://

www.agustawestland.com/technicalbullettins. You may review a copy of the 

service information at the FAA, Office of the 

Regional Counsel, Southwest Region, 2601 

Meacham Blvd., Room 663, Fort Worth, 

Texas 76137. 

(2) The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

Emergency Airworthiness Directive 2013– 

0225–E, effective September 21, 2013. You 

may view the EASA AD at http://

www.regulations.gov in Docket No. FAA– 

2013–0881. 

(h) Subject 

Joint Aircraft Service Component (JASC): 

6400 Tail rotor system. 

Issued in Fort Worth, Texas, on October 16, 

2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–24937 Filed 10–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0262; Directorate 

Identifier 2013–NE–13–AD; Amendment 39– 

17548; AD 2013–16–10] 

RIN 2120–AA64 

Airworthiness Directives; Hamilton 

Standard Division and Hamilton 

Sundstrand Corporation Propellers 

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 Hamilton Standard 

Division model 6/5500/F and 24PF and 

Hamilton Sundstrand Corporation 

model 14RF, 14SF, 247F, and 568F 

series propellers. A maintenance 

manual number in paragraph (g) of 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 

October 25, 2013. The effective date for 

AD 2013–16–10 (78 FR 49660, August 

15, 2013) remains September 19, 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: 

Michael Schwetz, Aerospace Engineer, 

Boston Aircraft Certification Office, 

FAA, 12 New England Executive Park, 

Burlington, MA 01803; phone: 781– 

238–7761; fax: 781–238–7170; email: 

michael.schwetz@faa.gov. 

SUPPLEMENTARY INFORMATION: AD 2013– 

16–10, Amendment 39–17548 (78 FR 

49660, August 15, 2013), currently 

requires incorporating inspections, 

based on a calendar time, into the 

propeller maintenance schedule for 

Hamilton Standard Division model 6/

5500/F and 24PF and Hamilton 

Sundstrand Corporation model 14RF, 

14SF, 247F, and 568F series propellers. 


emcdonald on DSK67QTVN1PROD with RULES
Federal Register / Vol. 78, No. 207 / Friday, October 25, 2013 / Rules and Regulations 63853 

As published, the maintenance 

manual number, P4202, as part of the 

model/manual number, 247F–1/P4202, 

in paragraph (g) of the Compliance 

section is incorrect. 

No other part of the preamble or 

regulatory information has been 

changed; therefore, only the changed 

portion of the final rule is being 

published in the Federal Register. 

The effective date for AD 2013–16–10 

(78 FR 49660, August 15, 2013) remains 

September 19, 2013. 

Correction of Regulatory Text 

§ 39.13 [Corrected] 

■ In the Federal Register of August 15, 

2013, on page 49662, in the 1st column, 

paragraph (g) of AD 2013–16–10 is 

corrected to read as follows: 

* * * * * 

(g) MI for Blades and Hubs That Do Not 

Have an Updated ALS 

For Hamilton Standard Division 

propeller models 6/5500/F and 24PF 

and Hamilton Sundstrand Corporation 

propeller models 14RF–19, 14RF–37, 

14SF–11, 14SF–15, 14SF–23, 14SF–17, 

14SF–19, 247F–1, 247F–1E, 247F–3, 

568F–1, 568F–5, and 568F–7, that do 

not have an approved update to the 

ALS, within one year after the effective 

date of this AD, perform an MI on the 

blades and hubs no later than seven 

years after the DSI. The DSI will begin 

at initial installation after the most 

recent MI or initial installation after 

production. Guidance on the 

inspections can be found in the 

applicable Hamilton Standard Division 

models/manuals 6/5500/F/P5190 and 

24PF/61–12–01, and Hamilton 

Sundstrand Corporation models/

manuals 14RF–19/P5199, 14RF–37/

P5209, 14SF–11/P5196, 14SF–15/P5197, 

14SF–23/P5197, 14SF–17/P5198, 14SF– 

19/P5198, 247F–1/P5202, 247F–1E/

P5204, 247F–3/P5205, 568F–1/P5214, 

568F–5/P5203, and 568F–7/P5211. 

* * * * * 

Issued in Burlington, Massachusetts, on 

October 15, 2013. 

Colleen M. D’Alessandro, 

Assistant Directorate Manager, Engine & 

Propeller Directorate, Aircraft Certification 

Service. 

[FR Doc. 2013–25108 Filed 10–24–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0878; Directorate 

Identifier 2013–SW–033–AD; Amendment 

39–17625; AD 2013–21–01] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for 

Eurocopter Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350C, 

AS350D, AS350D1, AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and 

AS355NP helicopters. This AD requires 

certain inspections of each tail rotor 

pitch horn assembly (pitch horn) for a 

crack, and if there is a crack, before 

further flight, replacing the pitch horn 

with an airworthy pitch horn. This AD 

is prompted by a report of a crack in the 

yoke of a pitch horn. These actions are 

intended to detect a crack in the pitch 

horn to prevent failure of the pitch horn, 

loss of the anti-torque function, and 

subsequent loss of control of the 

helicopter. 

DATES: This AD becomes effective 

October 25, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain document listed in this AD 

as of October 25, 2013. 

We must receive comments on this 

AD by December 24, 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 AD, the foreign 

authority’s AD, any incorporated-byreference service information, 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 service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 N. Forum Drive, 

Grand Prairie, TX 75052; telephone 

(972) 641–0000 or (800) 232–0323; fax 

(972) 641–3775; or at http://

www.eurocopter.com/techpub. You may 

review the referenced service 

information at the FAA, Office of the 

Regional Counsel, Southwest Region, 

2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

FOR FURTHER INFORMATION CONTACT: 

Robert Grant, Aviation Safety Engineer, 

Safety Management Group, FAA, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5110; email 

robert.grant@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not provide you with notice and 

an opportunity to provide your 

comments prior to it becoming effective. 

However, 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 resulted from 

adopting this AD. The most helpful 

comments reference a specific portion of 

the AD, 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 them 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 

rulemaking during the comment period. 

We will consider all the comments we 

receive and may conduct additional 

rulemaking based on those comments. 

Discussion 

We are adopting a new AD for the 

specified Eurocopter helicopters. This 

AD requires visually inspecting each 


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