Federal Register / Vol. 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: 

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): 

2013–21–01 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 (P/N) 

350A121368.01, 350A121368.02, 

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

pitch horn, P/N 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 P/N or pitch horn P/N. 

(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 (EASB) 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, P/N 

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 EASB No. 05.00.74 or 

No. 05.00.65. 

(f) Special Flight Permits 

Special flight permits are prohibited. 

(g) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Safety Management 

Group, FAA, may approve AMOCs for this 

AD. Send your proposal to: 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. 

(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. 

(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 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) 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 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 October 7, 

2013. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2013–24816 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–2013–0863; Directorate 

Identifier 2013–NM–178–AD; Amendment 

39–17627; AD 2013–21–03] 

RIN 2120–AA64 

Airworthiness Directives; the Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 747–8F 

and 747–8 series airplanes. This AD 

requires a detailed inspection of the 

power control actuator (PCA) 

installation to determine if a bushing is 

installed, a general visual inspection 

between the horizontal stabilizer rear 

spar and the elevator front spar and 

between certain stabilizer stations for 

defects 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 ram air 

turbine system, and a determination that 

a bushing was not installed. We are 

issuing this AD to detect and correct 

non-installation of bushings. If the 


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bushings are not present, the stiffness of 

the load path will be decreased, which 

will cause wear of adjacent parts and 

increased freeplay of the elevator 

surfaces. Freeplay that exceeds 

acceptable limits could result in 

divergent flutter for certain maneuvers, 

which could lead to loss of 

controllability of the airplane. 

DATES: This AD is effective November 

12, 2013. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of November 12, 2013. 

We must receive comments on this 

AD by December 9, 2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

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

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE. 

Washington, DC 20590, between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425 227–1221. 

Examining the AD Docket 

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 street address for 

the Docket Office (phone: 800–647– 

5527) is in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: (425) 

917–6513; fax: (425) 917–6590; email: 

narinder.luthra@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We received a report of unusual noise 

coming from the left inboard elevator 

during a functional check of the ram air 

turbine system. When investigating the 

cause of the noise, the operator found 

too much freeplay in the left inboard 

elevator, which was traced to a missing 

bushing in the PCA installation. 

Another investigation found that the left 

inboard PCA had been disconnected 

from this airplane to replace the left 

elevator, which had been damaged 

before delivery. When the PCA was 

reconnected, however, the bushing was 

not installed. The operator did 

inspections of the PCA installation and 

of the PCA attachment lug assembly, 

and found no other defects or damage. 

This condition (if the bushing is not 

present), if not detected and corrected, 

could result in decreased stiffness of the 

load path, which will cause wear of 

adjacent parts and increased freeplay of 

the elevator surfaces. Freeplay that 

exceeds acceptable limits could result in 

divergent flutter for certain maneuvers, 

which could lead to loss of 

controllability of the airplane. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 747–27A2515, dated August 23, 

2013. For information on the procedures 

and compliance times, see this service 

information at http://

www.regulations.gov by searching for 

Docket No. FAA–2013–0863. 

FAA’s Determination 

We are issuing this AD 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. 

AD Requirements 

This AD requires accomplishing the 

actions specified in the service 

information described previously, 

except as discussed under ‘‘Differences 

Between the AD and the Service 

Information.’’ 

The FAA worked in conjunction with 

industry, under the Airworthiness 

Directives Implementation Aviation 

Rulemaking Committee, to enhance the 

AD system. One enhancement was a 

new process for annotating which steps 

in the service information are required 

for compliance with an AD. 

Differentiating these steps from other 

tasks in the service information is 

expected to improve an owner’s/

operator’s understanding of crucial AD 

requirements and help provide 

consistent judgment in AD compliance. 

The actions specified in the service 

information described previously 

include steps that are labeled as ‘‘RC’’ 

(required for compliance) because these 

steps have a direct effect on detecting, 

preventing, resolving, or eliminating an 

identified unsafe condition. 

As noted in the specified service 

information, steps labeled as ‘‘RC’’ must 

be done to comply with the AD. 

However, steps that are not labeled as 

‘‘RC’’ are recommended. Those steps 

that are not labeled as ‘‘RC’’ may be 

deviated from, done as part of other 

actions, or done using accepted methods 

different from those identified in the 

service information without obtaining 

approval of an alternative method of 

compliance (AMOC), provided the steps 

labeled as ‘‘RC’’ can be done and the 

airplane can be put back in a serviceable 

condition. Any substitutions or changes 

to steps labeled as ‘‘RC’’ will require 

approval of an AMOC. 

In addition, the phrase ‘‘corrective 

actions’’ is used in this AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between the AD and the 

Service Information 

Although Boeing Alert Service 

Bulletin 747–27A2515, dated August 23, 

2013, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, and indicates 

that this action is ‘‘RC,’’ this AD 

requires repairing those conditions in 

one of the following ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

FAA’s Justification and Determination 

of the Effective Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because risk analysis indicated that 

urgent action is required. Any airplane 

that is missing a bushing in the elevator 

PCA installation is operating at an 

unacceptable level of risk. If the bushing 


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is not present, the stiffness of the load 

path will be decreased, which will 

cause wear of adjacent parts and 

increased freeplay of the elevator 

surfaces. Freeplay that exceeds 

acceptable limits could result in 

divergent flutter for certain maneuvers, 

which could lead to loss of 

controllability of the airplane. 

Therefore, we find that notice and 

opportunity for prior public comment 

are impracticable and that good cause 

exists for making this amendment 

effective in less than 30 days. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety and 

was not preceded by notice and an 

opportunity for public comment. 

However, we invite you to send any 

written data, views, or arguments about 

this AD. Send your comments to an 

address listed under the ADDRESSES

section. Include the docket number 

FAA–2013–0863 and Directorate 

Identifier 2013–NM–178–AD at the 

beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this AD. 

Costs of Compliance 

We estimate that this AD affects 8 

airplanes of U.S. registry. 

We estimate the following costs to 

comply with this AD: 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspection .................................................. 5 work-hours × $85 per hour = $425 ....... N/A $425 $3,400 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

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 would not have federalism 

implications under Executive Order 

13132. This 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 that this AD: 

(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, 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 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): 

2013–21–03 the Boeing Company: 

Amendment 39–17627; Docket No. 

FAA–2013–0863; Directorate Identifier 

2013–NM–178–AD. 

(a) Effective Date 

This AD is effective November 12, 2013. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to the Boeing Company 

Model 747–8F and 747–8 series airplanes, 

certificated in any category, as identified in 

Boeing Alert Service Bulletin 747–27A2515, 

dated August 23, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 27, Flight Controls. 

(e) Unsafe Condition 

This AD was prompted by a report of 

unusual noise coming from the left inboard 

elevator during a functional check of the ram 

air turbine system, and a determination that 

a bushing was not installed. We are issuing 

this AD to detect and correct non-installation 

of bushings. If the bushings are not present, 

the stiffness of the load path will be 

decreased, which will cause wear of adjacent 

parts and increased freeplay of the elevator 

surfaces. Freeplay that exceeds acceptable 

limits could result in divergent flutter for 

certain maneuvers, which could lead to loss 

of controllability of the airplane. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Inspections and Corrective Actions 

Except as required by paragraph (h)(1) of 

this AD, at the time specified in paragraph 

1.E., ‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 747–27A2515, dated August 23, 

2013: Do a detailed inspection of the inboard 

elevator left and right power control actuator 

(PCA) installations to determine if a bushing 

is installed; and do a general visual 

inspection between the left and right 

horizontal stabilizer rear spar and the 

elevator front spar, and between stabilizer 


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station (STAB) (STA) 235 and 260 for defects 

and damage, and do all applicable corrective 

actions that are labeled as ‘‘RC’’ (Required for 

Compliance), in accordance with the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 747–27A2515, dated August 

23, 2013, except as required by paragraph 

(h)(2) of this AD. Doing the steps specified 

in Parts 1 and 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

747–27A2515, dated August 23, 2013, are 

required for compliance. Do all applicable 

corrective actions that are labeled as ‘‘RC’’ 

before further flight. 

(h) Exceptions to Service Information 

Specifications 

(1) Where Boeing Alert Service Bulletin 

747–27A2515, dated August 23, 2013, 

specifies a compliance time ‘‘after the 

original issue date of this service bulletin,’’ 

this AD requires compliance within the 

specified compliance time after the effective 

date of this AD. 

(2) Although Boeing Alert Service Bulletin 

747–27A2515, dated August 23, 2013, 

specifies to contact Boeing for repair 

instructions, and indicates that action is 

‘‘RC’’ (Required for Compliance), this AD 

requires repairing before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (i) of this 

AD. 

(i) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (j) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO-AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) Except as required by paragraph (h)(2) 

of this AD: If the service information contains 

steps that are labeled as ‘‘RC’’ (Required for 

Compliance), those steps must be done to 

comply with this AD; any steps that are not 

labeled as ‘‘RC’’ are recommended. Those 

steps that are not labeled as ‘‘RC’’ may be 

deviated from, done as part of other actions, 

or done using accepted methods different 

from those identified in the specified service 

information without obtaining approval of an 

AMOC, provided the steps labeled as ‘‘RC’’ 

can be done and the airplane can be put back 

in a serviceable condition. Any substitutions 

or changes to steps labeled as ‘‘RC’’ require 

approval of an AMOC. 

(j) Related Information 

For more information about this AD, 

contact Narinder Luthra, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 1601 

Lind Avenue SW., Renton, Washington 

98057–3356; phone: (425) 917–6513; fax: 

(425) 917–6590; email: narinder.luthra@

faa.gov. 

(k) 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) Boeing Alert Service Bulletin 747– 

27A2515, dated August 23, 2013. 

(ii) Reserved. 

(3) For Boeing service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data & 

Services Management, P.O. Box 3707, MC 

2H–65, Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; Internet https://

www.myboeingfleet.com. 

(4) You may view this service information 

at FAA, Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425 227–1221. 

(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 Renton, Washington, on 

September 30, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24812 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–2013–0500; Directorate 

Identifier 2012–SW–45–AD; Amendment 39– 

17624; AD 2013–20–18] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. (Bell) 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–05– 

09 for Bell Model 412, 412CF, and 

412EP helicopters. AD 2009–05–09 

required reidentifying each affected 

part-numbered main rotor yoke (yoke) 

on its data plate, reducing the 

retirement life of the reidentified yoke, 

and revising the Airworthiness 

Limitations section of the maintenance 

manual or the Instructions for 

Continued Airworthiness (ICAs) 

accordingly. This new AD retains the 

requirements of AD 2009–05–09 with 

the exception of the P/N marking 

location. This AD was prompted by 

fatigue analysis that shows the 

retirement life should be reduced on 

certain yokes. We are issuing this AD to 

correct the unsafe condition on these 

helicopters. 

DATES: This AD is effective November 

29, 2013. 

ADDRESSES: For service information 

identified in this AD, contact Bell 

Helicopter Textron, Inc., P.O. Box 482, 

Fort Worth, TX 76101; telephone (817) 

280–3391; fax (817) 280–6466; or at 

http://www.bellcustomer.com/files/. 

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 Kohner, ASW–170, Aviation 

Safety Engineer, Rotorcraft Directorate, 

Rotorcraft Certification Office, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5170, fax 

(817) 222–5783, email 7-avs-asw-170@

faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–05–09, 

Amendment 39–15833 (74 FR 11001, 

March 16, 2009). AD 2009–05–09 

applied to Bell Model 412, 412CF, and 


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