Federal Register / Vol. 74, No. 112 / Friday, June 12, 2009 / Rules and Regulations 27915 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE—Continued 

Agusta Alert Bollettino Tecnico Date For helicopter model 

No. 109S–12 ......................................................................... June 6, 2007 ........................................................................ A109S 

No. 119–21 ............................................................................ June 6, 2007 ........................................................................ A119 

Issued in Fort Worth, Texas on May 21, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–13566 Filed 6–11–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0484; Directorate 

Identifier 2008–SW–44–AD; Amendment 39– 

15924; AD 2009–12–01] 

RIN 2120–AA64 

Airworthiness Directives; Bell 

Helicopter Textron, Inc. Model 47, 47B, 

47B3, 47D, 47D1, 47E, 47G, 47G–2, 

47G–2A, 47G–2A–1, 47G–3, 47G–3B, 

47G–3B–1, 47G–3B–2, 47G–3B–2A, 

47G–4, 47G–4A, 47G–5, 47G–5A, 47H– 

1, 47J, 47J–2, 47J–2A, and 47K 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

specified Bell Helicopter Textron, Inc. 

(Bell) helicopters. This action requires 

visually inspecting each main rotor 

blade box beam clip (clip) for correct 

installation. This amendment is 

prompted by a report of a main rotor 

blade with an incorrectly installed clip. 

The actions specified in this AD are 

intended to prevent a main rotor blade 

spar crack as a result of an incorrectly 

installed clip, loss of a main rotor blade, 

and subsequent loss of control of the 

helicopter. 

DATES: Effective June 29, 2009. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of June 29, 

2009. 

Comments for inclusion in the Rules 

Docket must be received on or before 

August 11, 2009. 

ADDRESSES: Use one of the following 

addresses to submit comments on this 

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 AD from 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/. 

Examining the Docket: You may 

examine the docket that contains the 

AD, any comments, and other 

information 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 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. 

FOR FURTHER INFORMATION CONTACT: 

Michael Kohner, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Rotorcraft Certification Office, Fort 

Worth, Texas 76193–0170, telephone 

(817) 222–5170, fax (817) 222–5783. 

SUPPLEMENTARY INFORMATION: This 

amendment adopts a new AD for the 

specified Bell helicopters. This action 

requires visually inspecting each clip 

for correct installation. This amendment 

is prompted by a report of a main rotor 

blade with an incorrectly installed clip. 

This condition, if not corrected, could 

result in a main rotor blade spar crack, 

loss of a main rotor blade, and 

subsequent loss of control of the 

helicopter. 

We have reviewed Bell Alert Service 

Bulletin No. 47–08–25, dated May 26, 

2008 (ASB), which describes procedures 

for visually inspecting each clip on the 

affected main rotor blade for correct 

installation. The ASB specifies that a 

clip incorrectly installed may cause a 

main rotor blade spar crack. 

This unsafe condition is likely to exist 

or develop on other helicopters of these 

same type designs. Therefore, this AD is 

being issued to prevent a main rotor 

blade spar crack as a result of an 

incorrectly installed clip, loss of a main 

rotor blade, and subsequent loss of 

control of the helicopter. This AD 

requires visually inspecting the entire 

length of each clip on an affected main 

rotor blade by following specified 

portions of the ASB described 

previously. The short compliance time 

involved is required because the 

previously described critical unsafe 

condition can adversely affect the 

structural integrity and controllability of 

the helicopter. Therefore, visually 

inspecting each main rotor blade for an 

incorrectly installed clip within 10 

hours time-in-service and replacing any 

main rotor blade that has an incorrectly 

installed clip with an airworthy main 

rotor blade before further flight is a very 

short time period, and this AD must be 

issued immediately. 

Since a situation exists that requires 

the immediate adoption of this 

regulation, it is found that notice and 

opportunity for prior public comment 

hereon are impracticable, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

We estimate that this AD will affect 

1,130 helicopters. It will require a 

minimal amount of time to locate the 7 

affected blades. The visual inspection 

for an incorrectly installed clip will take 

about 5 work hours at an average labor 

rate of $80 per work hour. Required 

parts will cost about $42,640. Based on 

these figures, we estimate the total cost 

impact of the AD on U.S. operators to 

be $45,440 ($2,800 for labor costs and 

$42,640 in parts costs) assuming only 

one blade will need to be replaced in 

the helicopter fleet. 

Comments Invited 

This AD is a final rule that involves 

requirements that affect flight safety and 

was not preceded by notice and an 

opportunity for public comment; 

however, we invite you to submit any 

written data, views, or arguments 

regarding this AD. Send your comments 

to an address listed under ADDRESSES. 

Include ‘‘Docket No. FAA–2009–0484; 

27916 Federal Register / Vol. 74, No. 112 / Friday, June 12, 2009 / Rules and Regulations 

Directorate Identifier 2008–44–SW–AD’’ 

at the beginning of your comments. We 

specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

the AD. We will consider all comments 

received by the closing date and may 

amend the AD in light 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 AD. Using the 

search function of our docket Web site, 

you can find and read the comments to 

any of our dockets, including the name 

of the individual who sent 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). 

Regulatory Findings 

We have 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 that the 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 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, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

■ Accordingly, pursuant to the authority 

delegated to me by the Administrator, 

the Federal Aviation Administration 

amends part 39 of the Federal Aviation 

Regulations (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 to read as 

follows: 

2009–12–01 Bell Helicopter Textron, Inc.: 

Amendment 39–15924. Docket No. 

FAA–2009–15924; Directorate Identifier 

2008–SW–44–AD. 

Applicability: Model 47, 47B, 47B3, 47D, 

47D1, 47E, 47G, 47G–2, 47G–2A, 47G–2A–1, 

47G–3, 47G–3B, 47G–3B–1, 47G–3B–2, 47G– 

3B–2A, 47G–4, 47G–4A, 47G–5, 47G–5A, 

47H–1, 47J, 47J–2, 47J–2A, and 47K 

helicopters with a main rotor blade, installed, 

with a part number (P/N) and serial number 

(S/N), listed as follows, certificated in any 

category: 

Main rotor blade, P/N With a S/N of 

047–110–250–021 .... A–303, A–304, A– 

312, or A–316. 

047–110–250–023 .... A–298, A–301, or A– 

305. 

Compliance: Required as indicated, unless 

done previously. 

To prevent a main rotor blade spar crack 

as a result of an incorrectly installed main 

rotor blade box beam clip (clip), loss of a 

main rotor blade, and subsequent loss of 

control of the helicopter, do the following: 

(a) Within 10 hours time-in-service (TIS), 

visually inspect the entire length of each 

upper and lower clip of each main rotor 

blade from the main rotor blade tip to the 

root by following Part II of the 

Accomplishment Instructions, paragraphs 1. 

through 8., of Bell Helicopter Textron, Inc. 

Alert Service Bulletin No. 47–08–25, dated 

May 26, 2008 (ASB) and referring to the 

depictions in Figures 1 and 2 of the ASB and 

Figure 1 of this AD for correct installation. 

Note: Figure 3 of the ASB depicts a clip 

installed incorrectly. 

Federal Register / Vol. 74, No. 112 / Friday, June 12, 2009 / Rules and Regulations 27917 

(b) Before further flight, if you find a main 

rotor blade with an incorrectly installed clip, 

replace that unairworthy main rotor blade 

with an airworthy main rotor blade that has 

a clip that is installed correctly. 

(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, Rotorcraft 

Certification Office, FAA, ATTN: Michael 

Kohner, Aviation Safety Engineer, Rotorcraft 

Directorate, Fort Worth, Texas 76193–0170, 

telephone (817) 222–5170, fax (817) 222– 

5783. 

(d) Special flight permits may be issued 

under 14 CFR 21.197 and 21.199 to operate 

the helicopter to a location where the 

requirements of this AD can be done 

provided the onetime ferry flight does not 

exceed 5 hours TIS. 

(e) The visual inspection shall be done by 

following the specified portions of Bell 

Helicopter Textron, Inc., Alert Service 

Bulletin No. 47–08–25, dated May 26, 2008. 

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

76101, telephone (817) 280–3391, fax (817) 

280–6466, 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 

June 29, 2009. 

Issued in Fort Worth, Texas, on May 19, 

2009. 

Mark R. Schilling, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. E9–13563 Filed 6–11–09; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–0323 Directorate 

Identifier 2009–CE–012–AD; Amendment 

39–15937; AD 2009–12–14] 

RIN 2120–AA64 

Airworthiness Directives; AeromotIndustria Mecanico Metalurgica ltda. 

Model AMT–200 and AMT–300 Series 

Gliders 

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: 

It has been found that the coolant liquid 

EVANS NPG + is a flammable fluid. The 

engine liquid cooling system of the affected 

Aeromot aircrafts is not designed to operate 

with flammable liquids. Therefore, there is 

an unacceptable engine fire risk associated 

with the use of Evans NPG + fluid. 

DATES: This AD becomes effective July 

17, 2009. 

On July 17, 2009, 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 FURTHER INFORMATION CONTACT: Greg 

Davison, Glider Program Manager, FAA, 

Small Airplane Directorate, 901 Locust, 

Room 301, Kansas City, Missouri 64106; 

telephone: (816) 329–4130; fax: (816) 

329–4090. 


ER12JN09.000</GPH>