Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 13063 

Alert Service Bulletin No. 427–09–29, REV 

A, dated November 17, 2009. 

(2) Applicable to all SNs: As of April 14, 

2011 (the effective date of this AD), you may 

not install replacement tail rotor driveshaft 

hanger bracket, P/N 427–044–223–101, 

unless the bracket has been inspected and 

found free of cracks and has been reworked 

following Bell Helicopter Alert Service 

Bulletin No. 427–09–29, REV A, dated 

November 17, 2009. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone: 

(817) 222–5122; fax: (817) 222–5961. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, a federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(h) Refer to MCAI Transport Canada AD 

No. CF–2010–17, dated June 2, 2010; and 

Bell Helicopter Alert Service Bulletin No. 

427–09–29, REV A, dated November 17, 

2009, for related information. 

Material Incorporated by Reference 

(i) You must use Bell Helicopter Alert 

Service Bulletin No. 427–09–29, REV A, 

dated November 17, 2009, to do the actions 

required by this AD, unless the AD specifies 

otherwise. 

(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 Bell Helicopter Textron, 

Inc., P.O. Box 482, Fort Worth, TX 76101; 

telephone: (817) 280–2011; fax: (817) 280– 

2321; or at http://www.bellhelicopter.com. 

(3) You may review copies of the 

referenced service information at the 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 

816–329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on January 13, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–4468 Filed 3–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0891; Directorate 

Identifier 2009–SW–055–AD; Amendment 

39–16585, AD 2011–03–02] 

RIN 2120–AA64 

Airworthiness Directives; 

EUROCOPTER FRANCE Model 

SA330F, SA330G, and SA330J 

Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD results 

from mandatory continuing 

airworthiness information (MCAI) 

issued by an aviation authority of 

another country to identify and correct 

an unsafe condition on an aviation 

product. The MCAI describes the unsafe 

condition as: 

While adjusting the position of the pedal 

unit on a SA 330 helicopter, the copilot set 

the position beyond the end limit (‘‘tall pilot’’ 

position). This resulted in the separation of 

the pedal adjustment system and the pedals 

rocking forward. 

After investigation, it was determined that 

the Loctite bond on the ‘‘tall pilot’’ stop nut 

was damaged, most likely due to aging of the 

adhesive. The nut came loose and could no 

longer perform its stop function. The 

threaded rod of the adjustment system 

separated from the system. 

The separation of the adjustment system, if 

not corrected, could result in the loss of 

control of the pedal units, causing the 

helicopter to begin rotating. 

We are issuing this AD to require 

actions to correct the unsafe condition 

on these products. 

DATES: This AD becomes effective April 

14, 2011. 

On April 14, 2011, the Director of the 

Federal Register approved the 

incorporation by reference of certain 

publications listed in this AD. 

FOR FURTHER INFORMATION CONTACT: Gary 

B. Roach, Aerospace Engineer, FAA, 

Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; 

telephone: (817) 222–5130; fax: (817) 

222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on September 13, 2010 (75 FR 

55492). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

While adjusting the position of the pedal 

unit on a SA 330 helicopter, the copilot set 

the position beyond the end limit (‘‘tall pilot’’ 

position). This resulted in the separation of 

the pedal adjustment system and the pedals 

rocking forward. 

After investigation, it was determined that 

the Loctite bond on the ‘‘tall pilot’’ stop nut 

was damaged, most likely due to aging of the 

adhesive. The nut came loose and could no 

longer perform its stop function. The 

threaded rod of the adjustment system 

separated from the system. 

The separation of the adjustment system, if 

not corrected, could result in the loss of 

control of the pedal units, causing the 

helicopter to begin rotating. 

For the reasons described above, this 

Emergency AD requires a one-time functional 

test and modification (MOD 330A779820.00) 

of the pedal unit adjustment system. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 


jdjones on DSK8KYBLC1PROD with RULES
13064 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

Differences Between This AD and the 

MCAI or Service Information 

We have reviewed the MCAI and 

related service information and, in 

general, agree with their substance. But 

we might have found it necessary to use 

different words from those in the MCAI 

to ensure the AD is clear for U.S. 

operators and is enforceable. In making 

these changes, we do not intend to differ 

substantively from the information 

provided in the MCAI and related 

service information. 

We might also have required different 

actions in this AD from those in the 

MCAI in order to follow FAA policies. 

Any such differences are highlighted in 

a NOTE within the AD. 

Costs of Compliance 

We estimate that this AD will affect 6 

products of U.S. registry. We also 

estimate that it will take about 3 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $100 per 

product. 

Based on these figures, we estimate 

the cost of this AD to the U.S. operators 

to be $2,130 or $355 per product. 

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 

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. 

For the reasons discussed above, I 

certify 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); 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 a regulatory evaluation 

of the estimated costs to comply with 

this AD and placed it in the AD Docket. 

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 the NPRM, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(telephone (800) 647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

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: 

2011–03–02 EUROCOPTER FRANCE: 

Amendment 39–16585; Docket No. 

FAA–2010–0891; Directorate Identifier 

2009–SW–055–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to SA330F, SA330G, 

and SA330J helicopters, all serial numbers, 

certificated in any category, equipped with 

pedal position adjustment system 

modification (MOD 07.10.304). 

Subject 

(d) Air Transport Association of America 

(ATA) Code 67: Rotors Flight Control. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

While adjusting the position of the pedal 

unit on a SA 330 helicopter, the copilot set 

the position beyond the end limit (‘‘tall pilot’’ 

position). This resulted in the separation of 

the pedal adjustment system and the pedals 

rocking forward. 

After investigation, it was determined that 

the Loctite bond on the ‘‘tall pilot’’ stop nut 

was damaged, most likely due to aging of the 

adhesive. The nut came loose and could no 

longer perform its stop function. The 

threaded rod of the adjustment system 

separated from the system. 

The separation of the adjustment system, if 

not corrected, could result in the loss of 

control of the pedal units, causing the 

helicopter to begin rotating. 

For the reasons described above, this 

Emergency AD requires a one-time functional 

test and modification (MOD 330A779820.00) 

of the pedal unit adjustment system. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Within the next 10 hours time-inservice after April 14, 2011 (the effective date 

of this AD), do a functional test of the pedal 

unit adjustment system following paragraph 

2.B.1 of EUROCOPTER Emergency Alert 

Service Bulletin No. 67.18, dated August 3, 

2009. 

(2) If any non-conformity is found, before 

further flight, modify the pedal unit 

adjustment system following paragraphs 

2.B.2, 2.B.3 or 2.B.4, and 2.B.5 of 

EUROCOPTER Emergency Alert Service 

Bulletin No. 67.18, dated August 3, 2009 

(MOD 330A779820.00). 

(3) If any non-conformity is not found, 

within 3 months after April 14, 2011 (the 

effective date of this AD), modify the pedal 

unit adjustment system following paragraphs 

2.B.2, 2.B.3, and 2.B.5 of the EUROCOPTER 

Emergency Alert Service Bulletin No. 67.18, 

dated August 3, 2009 (MOD 330A779820.00). 

(4) If half-bushings are not available when 

complying with paragraph (f)(2) or (f)(3) of 

this AD, flights are authorized without halfbushings for up to 12 months after April 14, 

2011 (the effective date of this AD). 

(5) After 3 months after April 14, 2011 (the 

effective date of this AD), do not install a 

pedal position adjustment system, unless it 

has been modified (MOD 330A779820.00) in 

accordance with the requirements of this AD. 

FAA AD Differences 

Note: This AD differs from the MCAI and/ 

or service information as follows: No 

differences. 


jdjones on DSK8KYBLC1PROD with RULES
Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 13065 

Other FAA AD Provisions 

(g) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, Standards Office, 

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: Gary B. Roach, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 Meacham 

Blvd., Fort Worth, Texas 76137; telephone: 

(817) 222–5130; fax: (817) 222–5961. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(3) Reporting Requirements: For any 

reporting requirement in this AD, under the 

provisions of the Paperwork Reduction Act 

(44 U.S.C. 3501 et seq.), the Office of 

Management and Budget (OMB) has 

approved the information collection 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to MCAI European Aviation 

Safety Agency (EASA) Emergency AD No.: 

2009–0172–E, dated August 5, 2009; and, for 

related information. 

Material Incorporated by Reference 

(i) You must use EUROCOPTER Emergency 

Alert Service Bulletin No. 67.18, dated 

August 3, 2009, to do the actions required by 

this AD, unless the AD specifies otherwise. 

(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 Internet: 

http://www.eurocopter.com. 

(3) You may review copies of the 

referenced service information at the FAA, 

Office of the Regional Counsel, Southwest 

Region, 2601 Meacham Blvd., Room 663, Fort 

Worth, Texas 76137. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

Issued in Fort Worth, Texas, on January 10, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certificate Service. 

[FR Doc. 2011–4466 Filed 3–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0781; Directorate 

Identifier 2007–SW–49–AD; Amendment 39– 

16590; AD 2011–03–06] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France Model AS–365N2, AS 365 N3, 

and SA–365N1 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Eurocopter France 

(Eurocopter) model helicopters. This AD 

requires replacing the aluminum tail 

rotor (T/R) blade pitch control shaft 

with a steel T/R blade pitch control 

shaft. This AD is prompted by an 

incident involving a Eurocopter Model 

AS–365N2 helicopter on which there 

was a loss of control of the T/R due to 

a broken shaft. The actions specified by 

this AD are intended to prevent failure 

of the T/R blade pitch control shaft, loss 

of T/R control, and subsequent loss of 

control of the helicopter. 

DATES: Effective April 14, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of April 14, 

2011. 

ADDRESSES: You may get the service 

information identified in this AD from 

American Eurocopter Corporation, 2701 

Forum Drive, Grand Prairie, Texas 

75053–4005, telephone (800) 232–0323, 

fax (972) 641–3710, or at http:// 

www.eurocopter.com. 

Examining the Docket: You may 

examine the docket that contains this 

AD, any comments, and other 

information on the Internet at http:// 

www.regulations.gov or at the Docket 

Operations office, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC. 

FOR FURTHER INFORMATION CONTACT: Jim 

Grigg, Aviation Safety Engineer, Safety 

Management Group, Rotorcraft 

Directorate, FAA, 2601 Meacham Blvd., 

Fort Worth, Texas 76137, telephone 

(817) 222–5126, fax (817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On August 2, 2010 we issued a Notice 

of Proposed Rulemaking (NPRM) to 

amend 14 CFR part 39 to include an AD 

that would apply to the Eurocopter 

Model AS–365N2, AS 365 N3, and SA– 

365N1 helicopters, all serial numbers, 

with an aluminum T/R blade pitch 

control shaft, part number (P/N) 

365A33.6161.20 or P/N 

365A33.6161.21. That NPRM was 

published in the Federal Register on 

August 11, 2010 (75 FR 48618) and 

proposed to require replacing the 

aluminum T/R blade pitch control shaft 

with a steel T/R blade pitch control 

shaft. The actions specified by the 

NPRM are intended to prevent failure of 

the T/R blade pitch control shaft, loss of 

T/R control, and subsequent loss of 

control of the helicopter. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA AD No. 

2007–0220, dated August 13, 2007, to 

correct an unsafe condition for the 

Eurocopter Model AS–365N2, AS 365 

N3, and SA–365N1 helicopters, all 

serial numbers, equipped with an 

aluminum T/R blade pitch control shaft, 

P/N 365A33.6161.20 or P/N 

365A33.6161.21. EASA advises of an 

incident in which the pilot of a Model 

AS 365 N2 helicopter encountered a 

loss of control of the T/R, but executed 

an uneventful run-on landing. A 

subsequent investigation revealed that 

the T/R blade pitch control shaft, P/N 

365A33.6161.21, had broken in the 

main section of the shaft sliding area, 

which appeared to be damaged by 

peening. The origin of the crack, which 

developed under fatigue loading, could 

not be determined. However, accidental 

damage (i.e., shock impact), is believed 

to have caused the initiation of a crack. 

Related Service Information 

Eurocopter has issued Alert Service 

Bulletin No. 01.00.59, dated June 21, 

2007 (ASB), which specifies removing 

any T/R blade pitch control shaft, P/N 

365A33.6161.20 or P/N 

365A33.6161.21, and replacing it with a 

steel T/R blade pitch control shaft, P/N 

365A33.6214.20. EASA classified this 

ASB as mandatory and issued EASA AD 

No. 2007–0220, dated August 13, 2007, 

to ensure the continued airworthiness of 

these helicopters. 


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