2842 Federal Register / Vol. 76, No. 11 / Tuesday, January 18, 2011 / Proposed Rules 

the corresponding action specified in this 

AD. 

Alternative Methods of Compliance 

(AMOCs) 

(k)(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. Send information to ATTN: Dean 

Thompson, Aerospace Engineer, Systems and 

Equipment Branch, ANM–130S, FAA, Seattle 

ACO, 1601 Lind Avenue, SW., Renton, 

Washington 98057–3356; telephone (425) 

917–6409; fax (425) 917–6590. Information 

may be e-mailed to: 9-ANM-Seattle-ACOAMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

Issued in Renton, Washington on January 

10, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–862 Filed 1–14–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1303; Directorate 

Identifier 2010–SW–049–AD] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Model SA–365N, 

SA–365N1, AS–365N2, AS 365 N3, and 

SA–366G1 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA) DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for the 

specified Eurocopter model helicopters. 

This proposed AD would require an 

initial and recurring inspections of the 

inner angles and flanges of the 9-degree 

frame on the right-hand (RH) and lefthand (LH) sides for a crack. If a crack 

is found, this proposed AD would 

require, before further flight, repairing 

the frame. This proposed AD is 

prompted by the discovery of a crack in 

the 9-degree frame of a Eurocopter 

Model AS–365N2 helicopter. These 

cracks could also develop on the other 

specified model helicopters because 

they contain the same 9-degree frame. 

The actions specified by this proposed 

AD are intended to detect a crack in the 

9-degree frame to prevent loss of 

structural integrity and subsequent loss 

of control of the helicopter. 

DATES: Comments must be received on 

or before March 21, 2011. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

proposed AD: 

• 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. 

You may get the service information 

identified in this proposed 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. 

You may examine the comments to 

this proposed AD in the AD docket on 

the Internet at http:// 

www.regulations.gov. 

FOR FURTHER INFORMATION CONTACT: Gary 

Roach, Aviation Safety Engineer, FAA, 

Rotorcraft Directorate, Regulations and 

Policy Group, 2601 Meacham Blvd, Fort 

Worth, Texas 76137, telephone (817) 

222–5130, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the caption 

ADDRESSES. Include the Docket No. 

‘‘FAA–2010–1303, Directorate Identifier 

2010–SW–049–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed 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 with FAA 

personnel concerning this proposed 

rulemaking. Using the search function 

of the docket Web site, you can find and 

read the comments to any of our 

dockets, including the name of the 

individual who sent or signed the 

comment. You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

Examining the Docket 

You may examine the docket that 

contains the proposed AD, any 

comments, and other information in 

person at the Docket Operations office 

between 9 a.m. and 5 p.m., Monday 

through Friday, except Federal holidays. 

The Docket Operations office (telephone 

(800) 647–5527) is located in Room 

W12–140 on the ground floor of the 

West Building at the street address 

stated in the ADDRESSES section. 

Comments will be available in the AD 

docket shortly after receipt. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued Emergency AD 

No. 2010–0064–E, dated April 1, 2010, 

which supersedes EASA Emergency AD 

No. 2009–0125–E, dated June 12, 2009, 

and the correction dated June 15, 2009, 

to correct an unsafe condition for the 

specified model helicopters. EASA 

advises that during a major inspection a 

crack was found in the 9-degree frame 

of an AS–365N2 helicopter, which had 

logged a total of 10,786 flight hours. The 

crack was located 230 millimeters above 

the cabin floor and had grown over a 

large section of the 9-degree frame on 

the RH side. EASA states that analysis 

shows that the time required for 

initiation of a crack in this area varies 

according to the weight and balance 

data of the different aircraft versions. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin (EASB), Revision 

1, dated March 31, 2010, containing the 

following three numbers: No. 05.00.57 

for FAA type-certificated Model SA– 

365N, N1 and AS–365N2 and N3 

helicopters and for military, not FAA 

type-certificated, Model AS365F, Fs, Fi, 

and K helicopters; No. 05.00.25 for 

military, not FAA type-certificated, 

Model AS565AA, MA, MB, SA, SB, and 

UB helicopters; and No. 05.39 for FAA 

type-certificated Model SA–366G1 

helicopters and for military, not FAA 

type-certificated, Model SA366GA 

helicopters. The EASB specifies 

checking at regular intervals for a crack 

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in the areas of the inner angles and 

flanges of the 9° frame on the RH and 

LH sides, near the splice. The EASB 

states that Eurocopter is currently 

studying an improvement 

(reinforcement) of the frame, which will 

cancel the checks specified by the 

EASB. EASA classified this EASB as 

mandatory and issued AD No. 2010– 

0064–E, dated April 1, 2010, to ensure 

the continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

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, their 

technical representative, has notified us 

of the unsafe condition described in 

their AD. We are proposing 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. This proposed 

AD would require an initial and 

recurring inspections of the inner angles 

and flanges of the 9-degree frame on the 

RH and LH sides for a crack. If a crack 

is found, this proposed AD would 

require, before further flight, repairing 

the frame. 

Differences Between This Proposed AD 

and the EASA AD 

We refer to ‘‘flight hours’’ as ‘‘hours 

time-in-service.’’ We do not refer to the 

EASB for accomplishment instructions. 

We do not require contacting the 

manufacturer for approved repair 

instructions. We do not allow flight 

with a known crack. Therefore, we do 

not revise our required action based on 

the length and specific location of the 

crack on the 9-degree frame. We refer to 

the 9-degree frame rather than the No. 

9 frame. 

Costs of Compliance 

We estimate that this proposed AD 

would affect 19 helicopters of U.S. 

registry. We also estimate that it would 

take about 3 work hours for about 12 

inspections a year per helicopter. It 

would take about 24 hours to repair a 

helicopter frame. The average labor rate 

is $85 per work hour. Required parts 

would cost about $3,350. Based on these 

figures, we estimate the total cost 

impact of the proposed AD on U.S. 

operators to be $68,920 for the fleet, 

assuming 2 helicopters require repair 

each year. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. Additionally, this proposed 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 the proposed regulation: 

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 proposed AD. See the AD docket to 

examine the economic evaluation. 

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. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Safety. 

The Proposed 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. Section 39.13 is amended by 

adding a new airworthiness directive 

(AD) to read as follows: 

Eurocopter France: Docket No. FAA–2010– 

1303; Directorate Identifier 2010–SW– 

049–AD 

Applicability: Model SA–365N, SA–365N1, 

AS–365N2, AS 365 N3, and SA–366G1 

helicopters, certificated in any category. 

Compliance: Required as indicated. 

To detect a crack in the 9-degree frame to 

prevent loss of structural integrity and 

subsequent loss of control of the helicopter, 

do the following: 

(a) On or before the affected model 

helicopters reach the hours time-in-service 

(TIS) listed in Table 1 of this AD or within 

10 hours TIS, whichever occurs later, unless 

accomplished previously, and thereafter at 

intervals not to exceed 110 hours TIS, using 

a 10X or higher magnifying glass, inspect the 

inner angles and flanges of the 9-degree 

fuselage frame on the right hand and left 

hand sides for a crack in the area depicted 

in Figure 1 and as shown in Figure 2 of this 

AD. 

TABLE 1 

Helicopter model Hours TIS 

SA–365N .............................. 8,990 

SA–365N1 ............................ 9,990 

AS–365N2 ............................ 3,190 

AS 365 N3 ............................ 2,090 

SA–366G1 ............................ 9,990 

BILLING CODE 4910–13–P 

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BILLING CODE 4910–13–C 

Note 1: Eurocopter Emergency Alert 

Service Bulletin, Revision 1, dated March 31, 

2010 (EASB), containing the following 3 

numbers: No. 05.00.57 for FAA typecertificated Model SA–365N and N1 and AS– 

365N2 and N3 helicopters and for military, 

not FAA type-certificated, Model AS365F, 

Fs, Fi, and K helicopters; No. 05.00.25 for 

military, not FAA type-certificated, Model 

AS565AA, MA, MB, SA, SB, and UB 

helicopters; and No. 05.39 for FAA typecertificated Model SA–366G1 helicopters and 

for military, not FAA type-certificated, Model 

SA366GA helicopters. This EASB is not 

incorporated by reference but contains 

additional information about the subject of 

this AD. Actions previously done by 

following the procedures of this EASB are 

considered acceptable for complying with the 

corresponding actions in paragraphs (a) and 

(b) of this AD. 

(b) If you find a crack, before further flight, 

repair the frame. Repairing a frame does not 

constitute terminating action for the 

repetitive inspection requirements of this 

AD. 

(c) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Contact the Manager, Safety 

Management Group, FAA, ATTN: Gary 

Roach, Aviation Safety Engineer, Regulations 

and Policy Group 2601 Meacham Blvd, Fort 

Worth, Texas, 76137; telephone: (817) 222– 

5130 fax: 817–222–5961, for information 

about previously approved alternative 

methods of compliance. 

(d) The Joint Aircraft System/Component 

(JASC) Code is 5311: Fuselage Main, Frame. 

Note 2: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2010–0064–E, dated April 1, 2010. 

Issued in Fort Worth, Texas on December 

16, 2010. 

M. Monica Merritt, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–720 Filed 1–14–11; 8:45 am] 

BILLING CODE 4910–13–P 


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