**~"'~""""'"**
**1~** INFORMATION ' 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) ofthe Complia section is incorrect.

No other part ofthe pre regulatory information s been changed; therefore, o the changed portion ofthe 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.

• Inthe Federal Register ofAugust 15, 2013, on page 49662, inthe 1st column, paragraph (g) ofAD 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 approvedupdate to the ALS, within one year after the effective date ofthis AD, perform an MI onthe blades and hubs no later than seven years after the DSI. The DSI willbe · 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.

AssistantDirectorat 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 ofa crack in the yoke ofa pitch horn. These actions are intendedto detect a crack inthe pitch horn to prevent failure ofthe pitch horn, loss ofthe anti-torque function, and subsequent loss ofcontrol ofthe helicopter.

DATES: This AD becomes effective October 25, 2013.

The Director ofthe Federal Register approved the incorporationbyreference ofa certain document listed in this AD

as ofOctober 25, 2013.

We must receive comments on this AD by December 24, 2013.
ADDRESSES: You may send comments by any ofthe following methods:



### • Federal eRulemakingDocket: Go to 

### http://www.regulations.gov. Followthe online instructions for sending your comments electronically.

• Fax:202-493-2251.


### • Mail: Send comments to the U.S. Department ofTransportation, Docket Operations, M-30, West Building Ground Floor, Room W12-140, 1200 NewJersey Avenue SE., Washington, DC 20590-0001.



### • HandDelivery: 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 inthe 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 ofthe 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 rulemakingby 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 ofwritten comments, or ifcomments 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 

### IFriday, October 25, 2013/Rules and Regulations

pitch horn for a crack. This AD also requires, ifthere is a crack, before further flight, replacing the pitch horn with an airworthy pitch horn. This AD is promptedby a report ofa crack inthe yoke ofa pitch horn. These actions are intendedto detect a crackinthe pitch horn to prevent failure ofthe pitch horn, loss ofthe anti-torque function, and subsequent loss ofcontrol ofthe helicopter.

The EuropeanAviation Safety Agency (EASA), which is the TechnicalAgent for the Member States oftheEuropean Union, has issuedEASA AD No. 2013- 0133, datedJune 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 ofan ongoing crack inthe yoke ofa which a cause has not The EASA AD requires inspections ofeach pitch crack and replacing the

a serviceable assembly found. EASA states interim action and follow.
FAA'sDetermination

These helicopters havebeen approved by the aviation authority ofFrance and

are approved for operation inthe United States. Pursuantto ourbilateral agreement with France, EASA, its technical representative, has notified us oftheunsafe condition described inthe EASA AD. We are issuing this AD becausewe evaluated all information providedbyEASA and determinedthe unsafe condition exists and is likely to exist or develop on other helicopters of these sametype designs.
Related Service Information

Eurocopter has issued oneEmergency 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 certificatedModel AS350BB; andthe non-FAA type certificated military Model AS350L1 helicopters. EASB No. 05.00.49 is for non-FAAtype certificated military Models AS550A2, C2, C3, andU2 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 ofa case ofa crack on the yoke ofa pitch horn, which may lead to failure ofthe pitchhorn, resulting in loss ofthe anti-torque function. The EASB specifies a checkfor cracks onthe yokes ofthetwo pitch horns and specifies replacing any cracked pitch horn. The EASB states that itmay be necessary to modify the log card ofthe tail rotorblade assembly dueto some of the pitch hornpartnumbers being recorded incorrectly.
AD Requirements

This AD requires:

• Based onthe 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 andtherefore is not
a part ofthis AD. The EASA AD does not apply to Eurocopter Model AS350C

or the AS350D1, butthis AD does becausethose models have an FAA type certificate and may have the applicable pitch horn installed. This AD requires a dye-penetrant inspectionbefore installing a pitchhorn; theEASA AD does not. TheEASA AD applies to parts with less than 135 hours TIS, whilethis AD does not. The EASA AD requires the pitch horn inspectionto berepeated every 165 flight hours, and this AD does not.
InterimAction

We considerthis AD to be an interim action. If

### final action is later identified,

we might consider further rulemaking then.
Costs ofCompliance

We estimate thatthis AD will affect 938 helicopters ofU.S. Registry. We estimate that operators may incurthe following costs to comply withthis AD. Labor costs are estimated at $85 per workhour. We estimate .1 workhourto visually inspect a pitch horn for a total of$8.50 perhelicopter and $7,973 for the fleet. We estimate 1 work hourto do

a dye-penetrant inspection, for a total cost of$85 perhelicopter. We estimate 1 workhourto replace a partif necessary, and a cost for required parts of$1,946, for a total cost of$2,031 per helicopter. 

### ., FAA'sJustification andDetermination ofthe Effective Date

Providing an opportunity for public comments before adopting these AD requirements would delay implementingthe safety actions needed to correct this knownunsafe condition. Therefore we find thattherisk to the flying publicjustifies :waiving notice and comment priorto ad,opting this rule becausethe corrective actions mustbe for**helicopter~** 

### flying

more than 155•hours TIS, a short**t~me** 

### average flight-1lour these helicopters. · .. , conditionexists that'
,u.,uHn" 

### adoption ofthis that notice and public commentbefore AD are impracticable and**~o** 

### the public interest and that good cause

..exists for making this amendment effective inless than 30 days. Authorityfor This Rulemaking

Title 49 ofthe United States Code specifies the FAA's authorityto issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. "Subtitle VU,: Aviation Programs," describes inmore-, detail the scope ofthe Agency's authority.

We are issuingthis rulemaking under the authority described in "Subtitle VII,**P~** 

### A, Subpart III, Section 44701: GenE!:r.qJ requirements." Underthat section,'Congress charges theFAA with promoting-safe flight ofcivil aircraft in air commerce

### by. prescribingregulations for practices, methods, andprocedures the Administrator finCI:s necessary for safety in air commerce. This regulation is withinthe scope ofthat autbprity because it addresses anunsafe**C()n,~ition** 

### that is likely to exist or develop on "'··. products identifiedinthis rulemaking ·,. action. Regulatory Findings

We determinedthatthis AD will not Hhvt:J federalism implications under Execb.tive Order 13132. This AD will not have a .substantial direct effect on the States,

# orrtherelationship between the national Government andthe States,

or on the distributidn ofpower and responsibilities amongthe various levels ofgovernment. ·

For thereasons discussed, I certify thatthis AD:

..

1. 

### Is not a "significantregulatory • action" underExecutive Order 12866;

2. Is not a "significantrule" 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 itjustifies 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 ofthe Regulatory Flexibility Act.

We prepared an economic evaluation ofthe estimated costs to comply with this AD and placed it in the AD docket.
List ofSubjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation byreference, Safety. Adoption ofthe 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. TheFAA 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 ofa pitch horn. This condition couldresult in failure ofa pitch horn, loss ofthe anti-torque function, and subsequent loss ofcontrol ofthe 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 alreadybeen 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 ofEurocopterEmergency 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) Ifthere is a crack, before further flight, replace the pitch horn with an airworthy pitch horn.

(3) Do not install a pitchhorn, 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 ofEASE 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 ofthis AD is addressed in European Aviation Safety Agency (EASA) No. AD 2013-0133, dated June 28, 2013. You may view the EASA AD onthe Internet at http://www.regulations.govin Docket No. FAA-2013-0878. (i) Subject

Joint Aircraft Service Component (JASC) Code: 6400 Tail Rotor. (j) Material Incorporated by Reference

(1) The Director ofthe Federal Register approved the incorporation byreference (IBR) ofthe 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 requiredby this AD, unless the AD specifies otherwise.

(i) EurocopterEmergency Alert Service Bulletin No. 05.00.74, Revision 1, dated June 25, 2013.

(ii) EurocopterEmergency 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 andboth datedJune 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 datedJune 25, 2013, which are not incorporatedbyreference 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 ofthe Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability ofthis 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, RotorcraftDirectorate, 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 ofthe power control actu r (PCA) installation to rmine ifa 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 promptedby a report ofunusual noise coming from the left inboard elevator during a functional check ofthe ra 1r turbine system, and a determina · n that

a bushing was not installed. issuing this AD to detect correct non-installation ofbu ngs. Ifthe

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