Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 57659 

§ 162.12 [Amended] 

■ 5. In § 162.12, paragraph (a) is 

amended by removing the citation 

‘‘§ 161.3’’ and adding the citation 

‘‘§ 161.4’’ in its place. 

Done in Washington, DC, this 16th 

day of September 2010. 

Kevin Shea, 

Acting Administrator, Animal and Plant 

Health Inspection Service. 

[FR Doc. 2010–23671 Filed 9–21–10: 12:08 pm] 

BILLING CODE 3410–34–S 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0426; Directorate 

Identifier 2009–SW–34–AD; Amendment 39– 

16433; AD 2010–19–05] 

RIN 2120–AA64 

Airworthiness Directives Eurocopter 

France (ECF) Model SA–365N1, AS– 

365N2, AS 365 N3, EC 155B, and 

EC155B1 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

specified ECF model helicopters. This 

AD results from a mandatory continuing 

airworthiness information (MCAI) AD 

issued by the aviation authority of the 

European Aviation Safety Agency 

(EASA). The MCAI AD reports the 

separation and loss of a stainless steel 

ring (75 millimeter (mm) in diameter) 

from a tail rotor blade (blade) sleeve 

resulting in severe, high-frequency 

vibrations, which can lead to damage to 

the fenestron blades, loss of yaw 

control, and subsequent loss of control 

of the helicopter. 

DATES: This AD becomes effective on 

October 27, 2010. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

October 27, 2010. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

regulations.gov or in person at the 

Docket Operations office, U.S. 

Department of Transportation, M–30, 

West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue, SE., 

Washington, DC between 9 a.m. and 

5 p.m. Monday through Friday, except 

Federal holidays. 

You may get the service information 

identified in this AD from American 

Eurocopter Corporation, 2701 Forum 

Drive, Grand Prairie, TX 75053–4005, 

telephone (800) 232–0323, fax (972) 

641–3710, or at http:// 

www.eurocopter.com. 

Examining the AD Docket: The AD 

docket contains the Notice of proposed 

rulemaking (NPRM), the economic 

evaluation, any comments received, and 

other information. The street address 

and operating hours for the Docket 

Operations office (telephone (800) 647– 

5527) are in the ADDRESSES section of 

this AD. Comments will be available in 

the AD docket shortly after they are 

received. 

FOR FURTHER INFORMATION CONTACT: 

DOT/FAA Southwest Region, Gary 

Roach, ASW–111, Aviation Safety 

Engineer, Rotorcraft Directorate, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone (817) 222–5130; fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued an NPRM to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified ECF model 

helicopters on April 14, 2010. That 

NPRM was published in the Federal 

Register on April 22, 2010 (75 FR 

20931). That NPRM proposed: 

• For the ECF Model SA–365N1, AS– 

365N2, and AS 365 N3 helicopters, 

within 50 hours time-in-service (TIS), 

and thereafter at intervals not to exceed 

10 hours TIS, inspecting each blade of 

the fenestron tail rotor to determine 

whether there has been any outward 

slippage (toward the shroud) of the 

stainless steel ring that is around the 

sleeve of each blade where the blade 

enters the fenestron hub. 

• For the ECF Model EC 155B or B1 

helicopters, within 50 hours TIS, and 

thereafter at intervals not to exceed 15 

hours TIS, inspecting each blade for 

slippage of the fenestron tail rotor to 

determine whether there has been any 

outward slippage (toward the shroud) of 

the stainless steel ring that is around the 

sleeve of each blade where the blade 

enters the fenestron hub. 

• If the stainless steel ring has slipped 

outward, before further flight, replacing 

the blade with an airworthy blade. 

Comments 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. We received no 

comment on the NPRM or on our 

determination of the cost to the public; 

however, since the issuance of the 

NPRM, the average labor rate has 

increased from $80 per work hour to 

$85 per work hour, resulting in an 

increase of $41 in costs of compliance. 

We have determined that this change 

does not significantly increase the 

economic burden on any AD operator 

nor does it increase the scope of the AD. 

Therefore, based on our review and 

evaluation of the available data, we have 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin No. 05A011 for the Model EC 

155B and B1 helicopters and No. 

05.00.49 for the Model SA–365N1, AS– 

365N2, and AS 365 N3 helicopters. Both 

service bulletins are dated March 1, 

2006. The service information specifies 

checking the blade sleeve for slippage of 

the stainless steel ring (75 mm in 

diameter) and replacing the blade if the 

stainless steel ring has slipped. The 

actions described in the MCAI AD are 

intended to correct the same unsafe 

condition as that identified in the 

service information. 

Differences Between This AD and the 

MCAI AD 

We refer to flying hours as hours timein-service. Also, we use ‘‘inspect’’ rather 

than ‘‘check’’ to describe the actions 

required by this AD. We use a different 

initial compliance time. 

Costs of Compliance 

We estimate that this AD will affect 

about 33 helicopters of U.S. registry. We 

also estimate that it will take about 15 

minutes per helicopter to inspect for 

slippage of the stainless steel ring of the 

blade sleeve. The average labor rate is 

$85 per work-hour. Based on these 

figures, we estimate the cost of the AD 

on U.S. operators is $701, assuming 

none of the blades are replaced. 

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 


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57660 Federal Register / Vol. 75, No. 183 / Wednesday, September 22, 2010 / Rules and Regulations 

because it addresses an unsafe condition 

that is likely to exist or develop on 

product(s) identified in this rulemaking 

action. 

Regulatory Findings 

We determined that 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. 

Therefore, I certify 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); and 

3. 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 AD: 

2010–19–05 Eurocopter France: 

Amendment 39–16433 ; Docket No. 

FAA–2010–0426; Directorate Identifier 

2009–SW–34–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on October 27, 2010. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model SA–365N1, 

AS–365N2, AS 365 N3, EC 155B, and 

EC155B1 helicopters, with a fenestron tail 

rotor blade (blade), part number 365A12– 

0060–01 or 365A12–0070–00, installed, 

certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) AD reports 

the separation and loss of a stainless steel 

ring (75 mm in diameter) from a blade sleeve 

resulting in severe, high-frequency 

vibrations, which can lead to damage to the 

fenestron blades, loss of yaw control, and 

subsequent loss of control of the helicopter. 

Actions and Compliance 

(e) Required as indicated: 

(1) For the Model SA–365N1, AS–365N2, 

and AS 365 N3 helicopters, within 50 hours 

time-in-service (TIS), unless done previously, 

and thereafter at intervals not to exceed 10 

hours TIS, inspect each blade of the fenestron 

tail rotor to determine whether there has 

been any outward slippage (toward the 

shroud) of the stainless steel ring that is 

around the sleeve of each blade where the 

blade enters the fenestron hub as depicted in 

Appendix 1 and by following the 

Accomplishment Instructions, paragraph 

2.B.1., of Eurocopter Alert Service Bulletin 

No. 05.00.49, dated March 1, 2006. 

(2) For the Model EC 155B or B1 

helicopters, within 50 hours time-in-service 

(TIS), unless done previously, and thereafter 

at intervals not to exceed 15 hours TIS, 

inspect each blade of the fenestron tail rotor 

to determine whether there has been any 

outward slippage (toward the shroud) of the 

stainless steel ring that is around the sleeve 

of each blade where the blade enters the 

fenestron hub as depicted in Appendix 1 and 

by following paragraph 2.B.1., of Eurocopter 

Alert Service Bulletin No. 05A011, dated 

March 1, 2006. 

(3) If the stainless steel ring has slipped 

outward, before further flight, replace the 

blade with an airworthy blade. 

Differences Between This AD and the MCAI 

AD 

(f) We refer to flying hours as hours timein-service. Also, we use ‘‘inspect’’ rather than 

‘‘check’’ to describe the action to be taken in 

the AD. We use a different initial compliance 

time. 

Other Information 

(g) Alternative Methods of Compliance 

(AMOCs): The Manager, Rotorcraft 

Directorate, Safety Management Group, Attn: 

DOT/FAA Southwest Region, Gary Roach, 

ASW–111, Aviation Safety Engineer, 

Regulations and Guidance Group, 2601 

Meacham Blvd., Fort Worth, Texas 76137, 

telephone (817) 222–5130, fax (817) 222– 

5961, has the authority to approve AMOCs 

for this AD, if requested using the procedures 

found in 14 CFR 39.19. 

Related Information 

(h) European Aviation Safety Agency 

MCAI Airworthiness Directive No. 2006– 

0099, dated April 24, 2006, contains related 

information. 

Joint Aircraft System/Component (JASC) 

Code 

(i) The JASC Code is 6400: Tail Rotor. 

Material Incorporated by Reference 

(j) You must use the specified portions of 

Eurocopter Alert Service Bulletins No. 

05A011 and No. 05.00.49, both dated March 

1, 2006, to do the actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

this service information under 5 U.S.C. 

552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact American Eurocopter 

Corporation, 2701 Forum Drive, Grand 

Prairie, TX 75053–4005, telephone (800) 

232–0323, fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

(3) You may review copies at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Fort Worth, 

Texas 76137; or 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/ibr-locations.html. 

Issued in Fort Worth, Texas, on September 

3, 2010. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2010–23098 Filed 9–21–10; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0811; Directorate 

Identifier 2008–NE–41–AD; Amendment 39– 

16429; AD 2010–19–01] 

RIN 2120–AA64 

Airworthiness Directives; Rolls-Royce 

Corporation (RRC) AE 3007A Series 

Turbofan Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: The FAA is superseding an 

existing airworthiness directive (AD) for 

RRC AE 3007A series turbofan engines. 

That AD currently requires performing 

an eddy current inspection (ECI) or 

surface wave ultrasonic test (SWUT) 

inspection on each affected highpressure turbine (HPT) wheel. This AD 

requires removing or performing initial 

and repetitive ECIs or SWUT 

inspections on HPT stage 2 wheels for 

cracks. This AD also reduces the 

approved life limits of certain HPT stage 

2 wheels. This AD results from reports 

of cracked HPT stage 2 wheels. We are 

issuing this AD to prevent uncontained 

failure of the HPT stage 2 wheel and 

damage to the airplane. 

DATES: This AD becomes effective 

October 27, 2010. The Director of the 

Federal Register approved the 

incorporation by reference of certain 


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