53324 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

206–766–5680; e-mail 

me.boecom@boeing.com; Internet https:// 

www.myboeingfleet.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. 

(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 an NARA facility, 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 August 

12, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–21617 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0823; Directorate 

Identifier 2011–SW–018–AD; Amendment 

39–16765; AD 2011–17–01] 

RIN 2120–AA64 

Airworthiness Directives; Agusta 

S.p.A. Model A109A, A109A II, A109C, 

and A109K2 Helicopters 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment supersedes 

an existing emergency airworthiness 

directive (EAD) for the specified Agusta 

S.p.A. (Agusta) model helicopters. That 

EAD currently requires inspecting the 

main rotor scissor fitting assembly to 

determine if there are 2 washers 

installed under the head of each main 

rotor scissor fitting assembly fixing bolt 

(fixing bolt). If there are not 2 washers 

installed under the head of each fixing 

bolt, that EAD requires replacing each 

fixing bolt and installing 2 washers 

under the head of each fixing bolt. This 

superseding airworthiness directive 

(AD) is prompted by the determination 

that a wrong part number (P/N) for the 

main rotor scissor fitting assembly was 

listed in the EAD. This AD retains the 

requirements of the EAD and corrects a 

P/N for the main rotor scissor fitting 

assembly. The actions specified by this 

AD are intended to prevent a crack in 

a fixing bolt, failure of a fixing bolt, and 

subsequent loss of control of the 

helicopter. 

DATES: Effective September 12, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

12, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 25, 2011. 

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 Agusta 

Westland, Customer Support & Services, 

Via Per Tornavento 15, 21019 Somma 

Lombardo (VA) Italy, ATTN: Giovanni 

Cecchelli; telephone 39- 0331–711133; 

fax 39 0331 711180; or at http:// 

www.agustawestland.com/technicalbullettins. 

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: 

DOT/FAA Southwest Region, Sharon 

Miles, Aviation Safety Engineer, 

Rotorcraft Directorate, Regulations and 

Policy Group, ASW–111, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5122, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On January 13, 2010, we issued EAD 

2010–02–51 for the Agusta Model 

A109A, A109A II, A109C, and A109K2 

helicopters, which requires, within 5 

hours time-in-service (TIS), inspecting 

the main rotor scissor fitting assembly, 

P/N 109–0110–67 and P/N 109–0110– 

58, to determine if there were 2 washers 

installed under the head of each fixing 

bolt, P/N 109–0101–78–5. That action 

was prompted by an incident where 2 

of the 3 installed fixing bolts on a Model 

A109K2 helicopter had cracked in 

flight. The manufacturer’s investigation 

revealed that the crack was caused by 

inadequate information in the technical 

publication for installing the fixing 

bolts. This condition, if not detected 

and corrected, could result in failure of 

a fixing bolt and subsequent loss of 

control of the helicopter. 

Since issuing EAD 2010–02–51, we 

have determined that the EAD contains 

an incorrect P/N for the main rotor 

scissor fitting assembly as listed in 

paragraph (a) of the Compliance section. 

The EAD states P/N ‘‘109–0110–58’’ and 

the correct P/N is ‘‘109–0101–58’’. 

Therefore, we are issuing this 

superseding AD to correct a P/N for the 

main rotor scissor fitting assembly. 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Emergency AD 

2009–0274–E, dated December 18, 2009 

(EAD 2009–0274–E) to correct an unsafe 

condition for the Agusta Model A109A, 

A109A II, A109C, and A109K2 model 

helicopters. EASA states that failure of 

the fixing bolt ‘‘might lead to loss of 

control of the helicopter.’’ 

Related Service Information 

Agusta has issued Mandatory Alert 

Bollettino Tecnico (BT) No. 109K–53 for 

Model A109K2 helicopters and 

Mandatory Alert BT No. 109–131 for 

Model A109A, A109A II, and A109C 

helicopters, both dated December 18, 

2009. The BTs specify a one-time 

inspection for correct installation of the 

main rotor scissor fitting assembly by 

determining if 2 washers are installed 

under the head of each fixing bolt. If 2 

washers are not installed under the head 

of each fixing bolt, the BTs specify 

replacing each fixing bolt with an 

airworthy fixing bolt and installing 2 

washers under the head of each fixing 

bolt. EASA classified this service 

bulletin as mandatory and issued EAD 

No. 2009–0274–E 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 Italy, and 

are approved for operation in the United 

States. Pursuant to our bilateral 

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Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 53325 

agreement with Italy, EASA, their 

technical representative, has notified us 

of the unsafe condition described in the 

EASA emergency AD. We are issuing 

this superseding 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. Therefore, this AD is 

being issued to prevent a crack in a 

fixing bolt, failure of a fixing bolt, and 

subsequent loss of control of the 

helicopter. This AD requires, within 5 

hours TIS, inspecting the main rotor 

scissor fitting assembly to determine if 

there are two washers installed under 

the head of each fixing bolt. If 2 washers 

are not installed under the head of each 

fixing bolt, this AD requires, within 25 

hours TIS after making that 

determination, replacing all 3 fixing 

bolts and installing 2 washers under the 

head of each fixing bolt. The actions 

must be accomplished by following 

specified portions of the previously 

described service bulletins. 

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, because these actions are 

required within a very short period of 

time, 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 because of the 

short compliance time, and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Differences Between This AD and the 

EASA AD 

This AD differs from the EASA AD in 

that EASA uses the term ‘‘flight hours’’ 

when referring to compliance times, and 

we use the term ‘‘hours time-inservice’’. Also, after complying with 

paragraph (a) of this AD, we require the 

fixing bolts to be replaced within 25 

hours TIS, and the EASA AD requires 

the fixing bolts to be replaced within 25 

flight hours after the effective date of the 

AD or by April 30, 2010. 

Costs of Compliance 

We estimate that this AD will affect 

79 helicopters of U.S. registry. Each 

inspection will take about 15 minutes, 

and replacing a fixing bolt will take 

about 3 hours. The average labor rate is 

$85 per work-hour. Required parts will 

cost approximately $153 per helicopter 

for the bolts and washers. Based on 

these figures, we estimate the total cost 

on U.S. operators to be $4,943, assuming 

that each helicopter is inspected and 

that 8 helicopters require replacement of 

the 3 bolts and 6 washers. 

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–2011–0823; 

Directorate Identifier 2011–SW–018– 

AD’’ at the beginning of your comments. 

We specifically invite comments on the 

overall regulatory, economic, 

environmental, and energy aspects of 

this AD. We will consider all comments 

received by the closing date and may 

amend this 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 AD. 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 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, 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 

a new airworthiness directive (AD) to 

read as follows: 

2011–17–01 AGUSTA S.p.A. (Agusta): 

Amendment 39–16765; Docket No. 

FAA–2011–0823; Directorate Identifier 

2011–SW–018–AD; supersedes 

Emergency AD 2010–02–51, issued 

January 13, 2010. 

Applicability: Model A109A, A109A II, 

A109C, and A109K2 helicopters, certificated 

in any category. 

Compliance: Required as indicated, unless 

accomplished previously. 

To prevent a crack in a main rotor scissor 

fitting assembly fixing bolt (fixing bolt), 

failure of a fixing bolt, and subsequent loss 

of control of the helicopter, accomplish the 

following: 

(a) Within 5 hours time-in-service (TIS), 

inspect the main rotor scissor fitting 

assembly, part number (P/N) 109–0110–67 or 

P/N 109–0101–58, to determine if there are 

2 washers, P/N NAS1149C0432R and P/N 

NAS1149C0463R, installed under the head of 

each fixing bolt, P/N 109–0101–78–5, as 

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53326 Federal Register / Vol. 76, No. 166 / Friday, August 26, 2011 / Rules and Regulations 

depicted in Figure 1 of Agusta Mandatory 

Alert Bollettino Tecnico (BT) No. 109K–53 

for Model A109K2 helicopters, and 

Mandatory Alert BT No. 109–131 for Model 

A109A, A109A II, and A109C helicopters, 

both dated December 18, 2009. 

(b) If 2 washers are not installed under the 

head of each fixing bolt, within 25 hours TIS 

of complying with paragraph (a) of this AD, 

replace each fixing bolt and install 2 washers 

under the head of each fixing bolt as depicted 

in Figures 1 and 2, and by following the 

Compliance Instructions, Part II, paragraphs 

1. through 3.5., of the BT for your helicopter. 

(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, ATTN: DOT/FAA 

Southwest Region, Sharon Miles, Aviation 

Safety Engineer, Rotorcraft Directorate, 

ASW–111, 2601 Meacham Blvd., Fort Worth, 

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

(817) 222–5961, for information about 

previously approved alternative methods of 

compliance. 

(d) The Joint Aircraft System/Component 

Code is 6220: Main Rotor Head. 

(e) The inspection and replacement shall 

be done in accordance with the specified 

portions of Agusta Mandatory Alert 

Bollettino Tecnico No. 109K–53 or Agusta 

Mandatory Alert Bollettino Tecnico No. 109– 

131, both dated December 18, 2009. 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 Agusta 

Westland, Customer Support & Services, Via 

Per Tornavento 15, 21019 Somma Lombardo 

(VA) Italy, ATTN: Giovanni Cecchelli; 

telephone 39–0331–711133; fax 39 0331 

711180; or at http:// 

www.agustawestland.com/technicalbullettins. 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 

September 12, 2011. 

Note: The subject of this AD is addressed 

in European Aviation Safety Agency (Italy) 

AD No. 2009–0274–E, dated December 18, 

2009. 

Issued in Fort Worth, Texas, on July 29, 

2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–21476 Filed 8–25–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0859 ; Directorate 

Identifier 2010–SW–052–AD; Amendment 

39–16777; AD 2011–17–13] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (ECF) Model EC120B 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for 

ECF Model EC120B helicopters. This 

action requires inserting an emergency 

procedure appendix from an ECF 

Emergency Alert Service Bulletin into 

the Rotorcraft Flight Manual (RFM). 

This action also requires modifying the 

emergency switch electrical wiring and 

performing tests to ensure correct 

operation of the emergency switch. This 

action also requires removing the 

emergency procedure appendix from the 

RFM after modifying the emergency 

switch electrical wiring and performing 

tests to ensure correct operation. This 

amendment is prompted by the 

discovery that simultaneously setting 

the emergency switch to the low 

position ‘‘CUT–OFF’’ and the generator 

(GENE) pushbutton to ‘‘OFF’’ position 

caused the starter-generator to restart. 

Investigation revealed that cross-wiring 

at the emergency switch caused this 

malfunction. This condition, if not 

corrected, could lead to the inability to 

isolate electrical equipment during an 

emergency, creating the risk of an 

uncontrolled electrical fire and 

subsequent loss of control of the 

helicopter. 

DATES: Effective September 12, 2011. 

The incorporation by reference of 

certain publications listed in the 

regulations is approved by the Director 

of the Federal Register as of September 

12, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

October 25, 2011. 

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 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. 

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: 

George Schwab, Aviation Safety 

Engineer, FAA, Rotorcraft Directorate, 

Safety Management Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137, telephone (817) 222–5114, fax 

(817) 222–5961. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA AD No. 2010– 

0078–E, dated April 23, 2010, to correct 

an unsafe condition for the ECF Model 

EC120B helicopters. EASA advises that 

while conducting a ‘‘smoke in the 

cockpit’’ procedure, ECF found that 

setting the emergency switch to CUT– 

OFF and the GENE pushbutton to OFF 

at the same time caused the aircraft 

starter-generator to ‘‘cut-in again.’’ 

Technical investigations revealed that 

cross-wiring at the emergency switch 

caused the malfunction. In this 

configuration, the ‘‘smoke in the 

cockpit’’ procedure described in the 

RFM does not isolate the equipment 

electrical power supply. 

Related Service Information 

ECF has issued Emergency Alert 

Service Bulletin No. 24A012, dated 

April 22, 2010 (EASB), which specifies 

modifying the emergency switch 

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