Federal Register / Vol. 74, No. 112 / Friday, June 12, 2009 / Rules and Regulations 27913 

requirements and has assigned OMB Control 

Number 2120–0056. 

Related Information 

(h) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) European 

Aviation Safety Agency Airworthiness 

Directive 2008–0218, dated December 10, 

2008; and Avions de Transport Regional 

Service Bulletins ATR42–92–0020 and 

ATR72–92–1021, both dated October 17, 

2008; for related information. 

Material Incorporated by Reference 

(i) You must use Avions de Transport 

Regional Service Bulletin ATR42–92–0020, 

dated October 17, 2008; or Avions de 

Transport Regional Service Bulletin ATR72– 

92–1021, dated October 17, 2008; as 

applicable; 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 ATR–GIE Avions de 

Transport Re ́gional, 1, Alle ́e Pierre Nadot, 

31712 Blagnac Cedex, France; telephone +33 

(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18; 

e-mail continued.airworthiness@atr.fr; 

Internet http://www.aerochain.com. 

(3) You may review copies of the service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue, SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221 or 425–227–1152. 

(4) You may also review copies of the 

service information that is incorporated by 

reference 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 Renton, Washington, on June 2, 

2009. 

Stephen P. Boyd, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. E9–13573 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–2009–0226; Directorate 

Identifier 2007–SW–35–AD; Amendment 39– 

15930; AD 2009–12–07] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Model A109E, A109S, A119, and 

AW119MKII Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for Agusta 

S.p.A. (Agusta) Model A109E, A109S, 

A119, and AW119MKII helicopters. 

This AD results from mandatory 

continuing airworthiness information 

(MCAI) originated by an aviation 

authority of another country to identify 

and correct an unsafe condition on an 

aviation product. The European 

Aviation Safety Agency (EASA), the 

Technical Agent for the aviation 

authority of Italy, with which we have 

a bilateral agreement, has issued an 

MCAI AD which states that two cases of 

cracks on a certain cargo hook lever 

(lever) have been reported by the 

manufacturer of the cargo hook. This 

lever is a critical structural component 

of the cargo hook, and a crack could 

result in inadvertent loss of the cargo 

hook load. This AD requires actions that 

are intended to address the unsafe 

condition caused by cracks in the cargo 

hook lever. 

DATES: This AD becomes effective on 

July 17, 2009. 

The incorporation by reference of 

certain publications is approved by the 

Director of the Federal Register as of 

July 17, 2009. 

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 Agusta, Via 

Giovanni Agusta, 520 21017 Cascina 

Costa di Samarate (VA), Italy, telephone 

39 0331–229111, fax 39 0331–229605/ 

222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 

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: John 

Strasburger, Aviation Safety Engineer, 

FAA, Rotorcraft Directorate, Regulations 

and Policy Group, 2601 Meacham Blvd., 

Fort Worth, Texas 76137; telephone 

(817) 222–5167; 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 Agusta Model A109E, 

A109S, A119, and AW119MKII 

helicopters on March 4, 2009. That 

NPRM was published in the Federal 

Register on March 23, 2009 (74 FR 

12096). That NPRM proposed to require 

actions that are intended to detect a 

crack in the cargo hook lever and 

prevent the inadvertent loss of the cargo 

hook load. You may obtain further 

information by examining the MCAI and 

any related service information in the 

AD docket. 

Comments 

By publishing the NPRM, we gave the 

public an opportunity to participate in 

developing this AD. However, we 

received no comment on the NPRM or 

on our determination of the cost to the 

public. 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. 

Relevant Service Information 

Agusta has issued Alert Bollettino 

Tecnico (ABT) No. 109EP–78, ABT No. 

109S–12, and ABT No. 119–21, all dated 

June 6, 2007. The actions described in 

the MCAI are intended to correct the 

same unsafe condition as that identified 

in the service information. 

Differences Between This AD and the 

MCAI 

We have reviewed the MCAI and, in 

general, agree with its substance. 

However, we have made the following 

changes: 

• Excluded the August 31, 2007 

compliance date because that date has 

passed; 

• Excluded the Model A109LUH from 

the applicability and do not reference 

Agusta ABT No. 109L–006 because the 

Model A109LUH helicopter is not on 

the U.S. type certificate, H7EU; 

• Added the Model AW119MKII to 

the applicability; 

• Required the use of a 10-power or 

higher magnifying glass to accomplish 

the visual inspections; and 

• Excluded the kit installation part 

number (P/N), relying instead on the 

cargo hook and lever P/N. 

These differences are highlighted in 

the ‘‘Differences Between this AD and 

the MCAI’’ section in this AD. 

Costs of Compliance 

We estimate that this AD will affect 

about 26 helicopters on the U.S. 

27914 Federal Register / Vol. 74, No. 112 / Friday, June 12, 2009 / Rules and Regulations 

Registry with the cargo hook. We also 

estimate that it will take about 10 

minutes to inspect each cargo hook for 

a crack, and about 1 work-hour to 

replace a cracked cargo hook. The 

average labor rate is $80 per work-hour. 

Required parts will cost about $3,677 

per cargo hook. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $97,647 per year, 

assuming that each affected helicopter 

requires five inspections per week, and 

that two cargo hooks are replaced each 

year. 

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 

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: 

2009–12–07 Agusta S.p.A.: Amendment 39– 

15930; Docket No. FAA–2009–0226; 

Directorate Identifier 2007–SW–35–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective on July 17, 2009. 

Other Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Model A109E, 

A109S, A119, and AW119MKII helicopters 

with cargo hook, part number (P/N) 528– 

010–01, and cargo hook lever, P/N 232–028– 

00, installed, certificated in any category. 

Reason 

(d) The mandatory continuing 

airworthiness information (MCAI) states that 

two cases of cracks in the lever, P/N 232– 

028–00, have been reported by the 

manufacturer of the cargo hook. The lever is 

a component of the cargo hook, P/N 528– 

010–01. This lever is a critical structural 

component of the cargo hook, and a crack 

could result in inadvertent loss of the cargo 

hook load. 

Actions and Compliance 

(e) Before each cargo hook operation, 

visually inspect the cargo hook lever, P/N 

232–028–00, for any crack. Use a 10-power 

or higher magnifying glass and inspect in the 

area depicted in Figures 1 and 2 of the 

following Agusta Alert Bollettino Tecnico 

(ABT), all dated June 6, 2007: 

(1) ABT No. 109EP–78 for Model A109E 

helicopters; 

(2) ABT No. 109S–12 for Model A109S 

helicopters; or 

(3) ABT No. 119–21 for Model A119 

helicopters. 

(f) If a crack is found in the lever, do not 

use the cargo hook until the entire cargo hook 

is replaced with an airworthy cargo hook 

with an uncracked lever. 

Differences Between This AD and the MCAI 

(g) This AD differs from the MCAI AD in 

that we: 

(1) Exclude the August 31, 2007 

compliance date because that date has 

passed; 

(2) Exclude the Model A109LUH from the 

applicability and do not reference Agusta 

ABT No. 109L–006 because the Model 

A109LUH helicopter is not on the U.S. type 

certificate, H7EU; 

(3) Add the Model AW119MKII to the 

applicability; 

(4) Require the use of a 10-power or higher 

magnifying glass to accomplish the visual 

inspections; and 

(5) Exclude the kit installation P/N, relying 

instead on the cargo hook and lever P/N. 

Other Information 

(h) Alternative Methods of Compliance 

(AMOCs): The Manager, Safety Management 

Group, 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: John Strasburger, 

Aviation Safety Engineer, Regulations and 

Policy Group, Rotorcraft Directorate, FAA, 

2601 Meacham Blvd., Fort Worth, TX 76137; 

telephone (817) 222–5167; fax (817) 222– 

5961. 

Related Information 

(i) EASA Emergency AD No. 2007–0160–E, 

dated June 7, 2007, contains related 

information. 

Air Transport Association of America (ATA) 

Tracking Code 

(j) Air Transport Association of America 

(ATA) Code 2550: Cargo Compartments. 

Material Incorporated by Reference 

(k) You must use the specified portions of 

the service information identified in Table 1 

to do the actions required. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

the service information identified in Table 1 

under 5 U.S.C. 552(a) and 1 CFR part 51. 

(2) For service information identified in 

this AD, contact Agusta, Via Giovanni 

Agusta, 520 21017 Cascina Costa di Samarate 

(VA), Italy, telephone 39 0331–229111, fax 39 

0331–229605/222595, or at http:// 

customersupport.agusta.com/ 

technical_advice.php. 

(3) You may review copies 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/ 

cfr/ibr-locations.html. 

TABLE 1—MATERIAL INCORPORATED BY REFERENCE

Agusta Alert Bollettino Tecnico Date For helicopter model 

No. 109EP–78 ....................................................................... June 6, 2007 ........................................................................ A109E 

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;