~"'~""""'" INFORMATION 

1~ ' 

CPO 

Federal Register/Vol. 78, No. 207 /Friday, October 25, 2013 /Rules and Regulations 63853 

As published, the maintenance 

manual number, P4202, as part ofth 

model/manual number, 247F-1/P 

in paragraph (g) of the Complia 

section is incorrect. 

No other part of the pre 

regulatory information s been 

changed; therefore, o the changed 

portion of the final le is being 

published in the ederal Register. 

The effecti date for AD 2013-16-10 

(78 FR 496 , August 15, 2013) remains 

Septem 19, 2013. 

• 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: 

* * * * 

ptlltJI"'ucJutl~ 14RF -1 

,14SF-15,1 

9,247F-1,24 

, 568F-5, and 56 

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 be · 

at initial installation after the 

recent MI or initial installat' 

production. Guidance o e 

inspections can be fo d in the 

applicable Hamil Standard Division 

models/man 6/5500/F/P5190 and 

24PF/61- 01, and Hamilton 

Sunds d Corporation models/ 

m als 14RF-19/P5199, 14RF-37/ 

209, 14SF-11/P5196, 14SF-15/P5197, 

14SF-23/P5197, 14SF-17/P5198,14SF19/P5198,247F-1/P5202,247F-1E/ 

P5204, 247F-3/P5205,568F-1/P5214, 

568F-5/P5203, and 568F-7 /P5211~ 

Issued in Burlington, Massach 

October 15, 2013. 

Assistant Directorat anager, Engine & 

te, Aircraft Certification 

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. 

for a 

before 

the pitch horn 

horn. This AD 

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:! I 

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, American Eurocopter 

N. Forum Drive, 

75052; telephone 

or(800)232-0323;fax 

orat .// 

. You may 

service 

FAA, Office of the 

Southwest Region, 

Blvd., Room 663, Fort 

exas 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 
63854 Federal Register I Vol. 78, No. 207 I Friday, October 25, 2013 /Rules and Regulations 

pitch horn for a crack. This AD also 

requires, 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 ofthe anti-torque function, and 

subsequent loss of control of the 

helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States ofthe European 

Union, has issued EASA AD No. 2013-

0133, dated June 28, 2013, to correct an unsafe condition for the Model AS350B, 

AS350BA, AS350BB, AS350B1, 

AS350B2, AS350B3, AS350D, AS355E, 

AS355F, AS355F1, AS355F2, AS355N, 

and AS355NP helicopters. EASA 

advises of an ongoing 

crack in the yoke of a 

which a cause has not 

The EASA AD requires 

inspections of each pitch 

crack and replacing the 

a serviceable assembly 

found. EASA states 

interim action and 

follow. 

FAA's Determination 

These helicopters have been approved 

by the aviation authority of France and are approved for operation in the United 

States. Pursuant to our bilateral 

agreement with France, EASA, its 

technical representative, has notified us 

of the unsafe condition described in the 

EASA AD. We are issuing this AD 

because we evaluated all information 

provided by EASA and determined the 

unsafe condition exists and is likely to 

exist or develop on other helicopters of 

these same type designs. 

Related Service Information 

Eurocopter has issued one Emergency 

Alert Service Bulletin, Revision 1, dated 

June 25, 2013 (EASB), with four 

different numbers. EASB No.05.00.74 is 

for Models AS350B, B1, B2, B3, BA, and 

D; the non-FAA type certificated Model 

AS350BB; and the non-FAA type 

certificated military Model AS350L1 

helicopters. EASB No. 05.00.49 is for 

non-FAA type certificated military 

Models AS550A2, C2, C3, and U2 

helicopters. EASB No. 05.00.65 is for 

Models AS355E, F, F1, F2, N, and NP 

helicopters. EASB No. 05.00.44 is for 

non-FAA type certificated military 

Model AS555AF, AN, SN, UF, and UN 

helicopters. Eurocopter has been 

informed of a case of a crack on the yoke 

of a pitch horn, which may lead to 

failure of the pitch horn, resulting in 

loss of the anti-torque function. The 

EASB specifies a check for cracks on the 

yokes of the two pitch horns and 

specifies replacing any cracked pitch 

horn. The EASB states that it may be 

necessary to modify the log card of the 

tail rotor blade assembly due to some of 

the pitch horn part numbers being 

recorded incorrectly. 

AD Requirements 

This AD requires: 

• Based on the hours time-in-service, 

within a specified time, visually 

inspecting each pitch horn for a 

the areas shown in Figure 1 

EASB. 

AD applies to Eurocopter 

AS350BB that does not have an 

FAA type certificate and therefore is not 

a part ofthis AD. The EASA AD does 

not apply to Eurocopter Model AS350C 

or the AS350D1, but this AD does 

because those models have an FAA type 

certificate and may have the applicable 

pitch horn installed. This AD requires a 

dye-penetrant inspection before 

installing a pitch horn; the EASA AD 

does not. The EASA AD applies to parts 

with less than 135 hours TIS, while this 

AD does not. The EASA AD requires the 

pitch horn inspection to be repeated 

every 165 flight hours, and this AD does 

not. 

Interim Action 

We consider this AD to be an interim 

action. If final action is later identified, 

we might consider further rulemaking 

then. 

Costs of Compliance 

We estimate that this AD will affect 

938 helicopters of U.S. Registry. We 

estimate that operators may incur the 

following costs to comply with this AD. 

Labor costs are estimated at $85 per 

work hour. We estimate .1 work hour to 

visually inspect a pitch horn for a total 

of $8.50 per helicopter and $7,973 for 

the fleet. We estimate 1 work hour to do 

a dye-penetrant inspection, for a total 

cost of $85 per helicopter. We estimate 

1 work hour to replace a part if 

necessary, and a cost for required parts 

of $1,946, for a total cost of $2,031 per 

helicopter. 

., 

FAA's Justification and Determination 

of the Effective Date 

Providing an opportunity for public 

comments before adopting these AD 

requirements would delay 

implementing the safety actions needed 

to correct this known unsafe condition. 

Therefore we find that the risk to the 

flying public justifies :waiving notice 

and comment prior to ad,opting this rule 

because the corrective actions must be 

for helicopter~ flying 

more than 155•hours 

TIS, a short t~me 

average flight-1lour 

these helicopters. · .. , 

condition exists that' 

,u.,uHn" adoption of this 

that notice and 

public comment before 

AD are impracticable and 

~o the public interest and that 

good cause .. exists for making this 

amendment effective in less than 30 

days. 

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 VU,: 

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, 

P~ A, Subpart III, Section 44701: 

GenE!:r.qJ 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 finCI:s necessary for 

safety in air commerce. This regulation 

is within the scope of that autbprity 

because it addresses an unsafe C()n,~ition 

that is likely to exist or develop on "'··. 

products identified in this rulemaking ·,. 

action. 

Regulatory Findings 

We determined that this AD will not 

Hhvt:J federalism implications under 

Execb.tive Order 13132. This AD will 

not have a .substantial direct effect on 

the States, orr the relationship between 

the national Government and the States, 

or on the distributidn of power and 

responsibilities among the various 

levels of government. · 

For the reasons discussed, 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); 
Federal Register/Val. 78, No. 207 /Friday, October 25, 2013 /Rules and Regulations 63855 

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: 

• 1. The authority 

continues to read as 

Authority: 49 U.S.C. 

§39.13 [Amended] 

• 2. The FAA amends§ 3 

the following new 

directive (AD): 

2013-21-01 Eurocopter France: 

Amendment 39-17625; Docket No. 

FAA-2013-0878; Directorate Identifier 

2013-SW-033-AD. 

(a) Applicability 

This AD applies to Eurocopter France 

(Eurocopter) Model AS350B, AS350BA, 

AS350B1, AS350B2, AS350B3, AS350C, 

AS350D, AS350D1, AS355E, AS355F, 

AS355F1, AS355F2, AS355N, and AS355NP 

helicopters with tail rotor hub pitch horn 

(pitch horn) assembly, part number (PIN) 

350A121368.01, 350A121368.02, 

350A121368.03, or 350A121368.04, with a 

pitch horn, PIN 350A121368.XX, where XX 

stands for two digit dash number, installed, 

certificated in any category. The pitch horn 

may be marked with either the pitch horn 

assembly PIN or pitch horn PIN. 

(b) Unsafe Condition 

This AD defines the unsafe condition as a 

crack in the yoke of a pitch horn. This 

condition could result in failure of a pitch 

horn, loss of the anti-torque function, and 

subsequent loss of control of the helicopter. 

(c) Effective Date 

This AD becomes effective October 25, 

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) For parts with 135 to 155 hours timein-service (TIS), before exceeding 165 hours 

TIS, or for parts with more than 155 hours 

TIS, within 10 hours TIS, visually inspect 

each pitch horn for a crack in the areas 

shown in Figure 1 of Eurocopter Emergency 

Alert Service Bulletin (EASE) No. 05.00.74 or 

No. 05.00.65, both Revision 1 and both dated 

June 25, 2013, as appropriate for your model 

helicopter. 

(2) If there is a crack, before further flight, 

replace the pitch horn with an airworthy 

pitch horn. 

(3) Do not install a pitch horn, PIN 

350A121368 (any dash number), on any 

helicopter unless it has passed a dye 

penetrant inspection for a crack in the areas 

shown in Figure 1 of EASE No. 05.00.74 

No. 05.00.65. 

rmlrll>rh•rl under a 14 

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 

The subject of this AD is addressed in 

European Aviation Safety Agency (EASA) 

No. AD 2013-0133, dated June 28, 2013. You 

may view the EASA AD on the Internet at 

http://www.regulations.gov in Docket No. 

FAA-2013-0878. 

(i) Subject 

Joint Aircraft Service Component (JASC) 

Code: 6400 Tail Rotor. 

(j) 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 G. 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) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.74, Revision 1, dated June 

25, 2013. 

(ii) Eurocopter Emergency Alert Service 

Bulletin No. 05.00.65, Revision 1, dated June 

25, 2013. 

Note to paragraph (j)(2): Eurocopter 

Emergency Alert Service Bulletin No. 

05.00.74 and No. 05.00.65, both Revision 1 

and both dated June 25, 2013, are copublished as one document along with 

Eurocopter Emergency Alert Service Bulletin 

No. 05.00.49 and No. 05.00.44, both Revision 

1 and both dated June 25, 2013, which are 

not incorporated by reference in this AD. 

(3) For Eurocopter service information 

identified in this AD, 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. 

(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 · this service information 

that is by reference at the 

and Records 

ARA). For information on 

this material at NARA, call 

to: http:!/ 

Texas, on October 7, 

ager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013-24816 Filed 10-24-13; 8:45am] 

BILLING CODE 4910-13-P 

DEPARTMENT OF TRANSPORTATI 

14 CFR Part 39 

(Docket No. FAA-20 -0863; Directorate 

Identifier 2013- -178-AD; Amendment 

39-17627;A 13-21-Q3] 

orthiness Directives; the Boeing 

ompany Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for tain 

The Boeing Company Model -8F 

and 747-8 series airplane his AD 

requires a detailed ins ction of the 

power control actu r (PCA) 

installation to rmine if a bushing is 

installed, a eral visual inspection 

between horizontal stabilizer rear 

spar the elevator front spar and 

een certain stabilizer stations for 

feels and damage, and corrective 

actions if necessary. This AD was 

prompted by a report of unusual noise 

coming from the left inboard elevator 

during a functional check of the ra 1r 

turbine system, and a determina · n that 

a bushing was not installed. 

issuing this AD to detect correct 

non-installation of bu ngs. If the 
' 

•,