Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 13061 

Applicability: Model 206A, 206B, 206L, 

206L–1, 206L–3, 206L–4, 222, 222B, 222U, 

230, 407, 427, and 430 helicopters, with a tail 

rotor blade (blade) having a part number and 

serial number, installed, as listed in the Rotor 

Blades Inc. (RBI) document attached to the 

following Bell Helicopter Textron Alert 

Service Bulletins (ASBs), certificated in any 

category: 

ASB No. Revision Date Helicopter model 

206–07–116 ........................................................................... B .............. November 29, 2010 .............................. 206A and 206B Series. 

206L–07–148 ......................................................................... B .............. November 29, 2010 .............................. 206L, L–1, L–3, and L–4. 

222–07–106 ........................................................................... D .............. November 29, 2010 .............................. 222 and 222B. 

222U–07–77 .......................................................................... D .............. November 29, 2010 .............................. 222U. 

230–07–38 ............................................................................. D .............. November 29, 2010 .............................. 230. 

407–07–81 ............................................................................. B .............. November 29, 2010 .............................. 407. 

427–07–18 ............................................................................. B .............. November 29, 2010 .............................. 427. 

430–07–41 ............................................................................. D .............. November 29, 2010 .............................. 430. 

Compliance: Before further flight, unless 

accomplished previously. 

To prevent loss of a blade tip weight, loss 

of a blade, and subsequent loss of control of 

the helicopter, do the following: 

(a) Replace any affected blade with an 

airworthy blade. An airworthy blade is one 

that has a part number and a serial number 

that is not listed in the RBI document 

attached to each ASB listed in the 

Applicability section of this AD. 

(b) 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: Sharon 

Miles, Aviation Safety Engineer, Rotorcraft 

Directorate, Regulations and Policy Group, 

2601 Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax (817) 

222–5961, for information about previously 

approved alternative methods of compliance. 

(c) Special flight permits will not be 

issued. 

(d) The Joint Aircraft System/Component 

(JASC) Code is: 6410—Tail Rotor Blades. 

(e) Determine the affected part number and 

serial number by referring to the RBI 

document attached to the following Bell 

Helicopter Textron Alert Service Bulletins, 

all dated November 29, 2010: 

Alert Service Bulletin No. Revision 

206–07–116 .............................. B 

206L–07–148 ............................ B 

222–07–106 .............................. D 

222U–07–77 ............................. D 

230–07–38 ................................ D 

407–07–81 ................................ B 

427–07–18 ................................ B 

430–07–41 ................................ D 

The Director of the Federal Register 

approved this incorporation by reference in 

accordance with 5 U.S.C. 552(a) and 1 CFR 

part 51. Copies may be obtained from Bell 

Helicopter Textron Canada Limited, 12,800 

Rue de l’Avenir, Mirabel, Quebec J7J1R4, 

telephone (450) 437–2862 or (800) 363–8023, 

fax (450) 433–0272, or at http:// 

www.bellcustomer.com/files/. Copies may be 

inspected at the FAA, Office of the Regional 

Counsel, Southwest Region, 2601 Meacham 

Blvd., Room 663, Fort Worth, Texas 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/ 

code_of_federal_regulations/ 

ibr_locations.html. 

(f) This amendment becomes effective on 

March 25, 2011, to all persons except those 

persons to whom it was made immediately 

effective by Emergency AD 2010–26–51, 

issued December 8, 2010, which contained 

the requirements of this amendment. 

Note: The subject of this AD is addressed 

in Transport Canada (Canada) AD CF–2007– 

21R1, dated November 30, 2010. 

Issued in Fort Worth, Texas, on January 14, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–4465 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–2010–0866; Directorate 

Identifier 2010–SW–065–AD; Amendment 

39–16586; AD 2011–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron Canada Limited 

Model 427 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: 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 

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. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

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. 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 FURTHER INFORMATION CONTACT: 

Sharon Miles, Aerospace Engineer, 

FAA, Rotorcraft Directorate, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5122; 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 August 30, 2010 (75 FR 

52912). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 


jdjones on DSK8KYBLC1PROD with RULES
13062 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 

The MCAI requires you to rework the 

tail rotor driveshaft hanger bearing 

bracket. 

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. 

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 

30 products of U.S. registry. We also 

estimate that it will take about 4 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Based on these figures, we estimate 

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

to be $10,200 or $340 per product. 

In addition, we estimate that any 

necessary follow-on actions would 

require parts costing $5,034, for a cost 

of $5,034 per product. We have no way 

of determining the number of products 

that may need these actions. 

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: 

2011–03–03 Bell Helicopter Textron 

Canada Limited: Amendment 39–16586; 

Docket No. FAA–2010–0866; Directorate 

Identifier 2010–SW–065–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective April 14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bell Helicopter 

Textron Canada Limited Model 427 

helicopters, all serial numbers (SNs), 

certificated in any category. 

Subject 

(d) Air Transport Association of America 

(ATA) Code 65: Tail Rotor Drive. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Tail rotor driveshaft hanger bearing bracket 

part number (P/N) 427–044–223–101 has 

been found cracked due to fatigue. It has 

been determined that the fatigue cracking 

was initiated by a tooling mark left during 

manufacture. 

The existence of tooling marks on the 

bracket could lead to bracket failure, loss of 

tail rotor drive and, consequently, loss of 

control of the helicopter. 

The MCAI requires you to rework the tail 

rotor driveshaft hanger bearing bracket. 

Actions and Compliance 

(f) Unless already done, do the following 

actions: 

(1) Applicable to SNs 56001 through 

56073, and 56077: Within 30 days after April 

14, 2011 (the effective date of this AD), 

inspect both sides of the hanger bracket, 

P/N 427–044–223–101, for cracks following 

Bell Helicopter Alert Service Bulletin No. 

427–09–29, REV A, dated November 17, 

2009. 

(i) If no cracks are found during the 

inspection required by paragraph (f)(1) of this 

AD, before further flight, rework both sides 

of the hanger bracket, P/N 427–044–223–101, 

following Bell Helicopter Alert Service 

Bulletin No. 427–09–29, REV A, dated 

November 17, 2009. 

(ii) If cracks are found during the 

inspection required by paragraph (f)(1) of this 

AD, before further flight, replace the hanger 

bracket, P/N 427–044–223–101, with a new 

hanger bracket, P/N 427–044–223–101, that 

has been reworked following Bell Helicopter 


jdjones on DSK8KYBLC1PROD with RULES
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