66618 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

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 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. 

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. The FAA amends § 39.13 by adding 

the following new airworthiness 

directive (AD): 

2011–21–12 Erickson Air-Crane 

Incorporated: Amendment 39–16835; 

Docket No. FAA–2010–0909; Directorate 

Identifier 2010–SW–026–AD. 

Applicability: Model S–64F helicopters, 

with rotating swashplate assembly 

(swashplate), part number (P/N) 65104– 

11001–051, installed, certificated in any 

category. 

Compliance: Required as indicated. 

To prevent loss of a swashplate due to a 

fatigue crack, loss of control of the main rotor 

system, and subsequent loss of control of the 

helicopter, do the following: 

(a) Within 15 hours time-in-service (TIS), 

unless accomplished previously, and 

thereafter at intervals not to exceed 15 hours 

TIS, clean and visually inspect the 

swashplate for a crack in areas A through F 

as depicted in Figure 1 of Erickson Air-Crane 

Service Bulletin 64B10–10, Revision 2, dated 

April 1, 2008 (SB). 

(b) Within 150 hours TIS, unless 

accomplished previously, and thereafter at 

intervals not to exceed 150 hours TIS, clean 

the swashplate and, using a 10-power or 

higher magnifying glass, visually inspect for 

a crack in areas A through F as depicted in 

Figure 1 of the SB. 

(c) Within 1,000 hours TIS since the last 

fluorescent-penetrant inspection (FPI) and 

thereafter at intervals not to exceed 1,000 

hours TIS, remove the swashplate from the 

rotor head, disassemble and remove the paint 

from the swashplate, and FPI the swashplate 

for a crack in accordance with ATSM E1417, 

Type I, Methods A or C. 

(d) If a crack is found in the swashplate, 

before further flight, replace the swashplate 

with an airworthy swashplate. 

(e) 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, Rotorcraft Directorate, 

ATTN: DOT/FAA Southwest Region, Michael 

Kohner, ASW–170, Aviation Safety Engineer, 

Fort Worth, Texas 76137, telephone (817) 

222–5170, fax (817) 222–5783, for 

information about previously approved 

alternative methods of compliance. 

(f) The Joint Aircraft System/Component 

(JASC) Code is 6230: Main Rotor Mast/ 

Swashplate. 

(g) The inspections shall be done in 

accordance with the specified portions of 

Erickson Air-Crane Service Bulletin 64B10– 

10, Revision 2, dated April 1, 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 Erickson AirCrane Incorporated, 3100 Willow Springs 

Road, P. O. Box 3247, Central Point, OR 

97502, telephone (541) 664–5544, fax (541) 

664–2312. 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. 

(h) This amendment becomes effective on 

December 1, 2011. 

Issued in Fort Worth, Texas, on September 

29, 2011. 

Kim Smith, 

Manager, Rotorcraft Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–27775 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1033; Directorate 

Identifier 2009–SW–43–AD; Amendment 39– 

16815; AD 2011–20–05] 

RIN 2120–AA64 

Airworthiness Directives; Eurocopter 

France (Eurocopter) Model EC225LP 

Helicopters 

AGENCY: Federal Aviation 

Administration, DOT. 

ACTION: Final rule; request for 

comments. 

SUMMARY: This amendment adopts a 

new airworthiness directive (AD) for the 

Eurocopter Model EC225LP helicopters. 

This AD requires inspecting the dome 

fairing support for a crack at the dome 

fairing attachment point. If a crack is 

found, this AD requires replacing the 

dome fairing support and the associated 

coning stop support assembly before 

further flight. If no crack is found, this 

AD requires repetitive inspections and 

retorquing the screws at specified 

intervals. This AD is prompted by the 

discovery of two fatigue cracks in the 

dome fairing attachment on the dome 

fairing support. This condition, if not 

corrected, could lead to the loss of the 

dome fairing in flight, causing damage 

to the helicopter and injury to people on 

the ground. 

DATES: Effective November 14, 2011. 

Comments for inclusion in the Rules 

Docket must be received on or before 

December 27, 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. 

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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66619 

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: Gary 

Roach, Aviation Safety Engineer, FAA, 

Regulations and Policy Group, 2601 

Meacham Blvd., Fort Worth, Texas 

76137; telephone: (817) 222–5130; 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 2009–0023, 

dated February 20, 2009, to correct an 

unsafe condition for the Eurocopter 

Model EC225LP helicopters. EASA 

advises that two fatigue cracks were 

discovered in the dome fairing 

attachment on the dome fairing support 

due to the loss of the tightening torque 

of the screws which secure the 

assembly. Since then, Eurocopter has 

developed a modification (MOD) which 

includes installation of redesigned parts 

with ‘‘modified geometrics’’ in the main 

rotor hub area. 

Related Service Information 

Eurocopter has issued Emergency 

Alert Service Bulletin No. 05A005, 

Revision 1, dated February 3, 2009 

(EASB 05A005), which applies to FAA 

type-certificated Model EC225LP 

helicopters and non-FAA type 

certificated Model EC725AP military 

helicopters. Eurocopter also issued 

Service Bulletin No. 62–007, Revision 1, 

dated July 10, 2009, which applies to 

FAA type-certificated Model EC225LP 

helicopters, and specifies reinforcing 

the cone restrainer support, MOD 

0743718. EASB 05A005 specifies 

checking the dome fairing support for a 

crack and readjusting the tightening 

torque of the dome fairing-to-dome 

fairing support attachment screws. If a 

crack is found, the EASB specifies 

complying with MOD 0743718 before 

resuming flight. Eurocopter states that 

installing this MOD exempts the 

operator from the monitoring 

requirements. They also state that this 

MOD reinforces the coning stop support 

and improves the dome fairing support 

attachment on the coning stop support. 

The EASA classified this service 

information as mandatory and issued 

EASA AD No. 2009–0023, dated 

February 20, 2009, to ensure the 

continued airworthiness of these 

helicopters. 

FAA’s Evaluation and Unsafe Condition 

Determination 

This helicopter model has been 

approved by the aviation authority of 

France and is approved for operation in 

the United States. Pursuant to our 

bilateral agreement with France, EASA, 

their technical representative, has 

notified us of the unsafe condition 

described in the EASA AD. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined an unsafe condition exists 

and is likely to exist or develop on other 

helicopters of the same type design. 

There are no products of this type 

currently registered in the United States. 

However, this rule is necessary to 

ensure that the described unsafe 

condition is addressed if any of these 

products are placed on the U.S. Registry 

in the future. 

Differences Between This AD and the 

EASA AD 

This AD differs from the EASA AD in 

that we: 

• Use ‘‘hours time-in-service’’ rather 

than ‘‘flight hours.’’ 

• Do not impose a calendar date 

compliance time. 

• Use the term ‘‘inspect’’ rather than 

‘‘check.’’ 

Costs of Compliance 

There are no costs of compliance 

since there are no helicopters of this 

type design on the U.S. Registry. 

FAA’s Determination of the Effective 

Date 

Since there are currently no affected 

U.S. registered helicopters, we have 

determined that notice and opportunity 

for prior public comment before issuing 

this AD are unnecessary and that good 

cause exists for making this amendment 

effective in less than 30 days. 

Requirements of This AD 

This unsafe condition is likely to exist 

or develop on other helicopters of the 

same type design registered in the 

United States. Therefore, this AD is 

being issued to prevent loss of the dome 

fairing in flight, causing damage to the 

helicopter and injury to people on the 

ground. This AD requires inspecting for 

a crack in the dome fairing support at 

the dome fairing attachment points. If a 

crack is found, this AD requires 

replacing the dome fairing support and 

the associated coning stop support 

assembly before further flight. If no 

crack is found, this AD requires 

repetitive inspections and retorquing 

the screws securing the dome fairing 

support to the dome fairing at specified 

intervals. This AD is prompted by the 

discovery of two fatigue cracks in the 

dome fairing attachment on the dome 

fairing support. Accomplishing 

Eurocopter MOD 0743718 constitutes 

terminating action for the requirements 

of this AD. 

Comments Invited 

This AD is a final rule that involves 

requirements affecting flight safety, and 

we did not precede it by notice and 

opportunity for public comment. We 

invite you to send any written relevant 

data, views, or arguments about this AD. 

Send your comments to an address 

listed under the ADDRESSES. Include 

‘‘Docket No. FAA–2011–1033; 

Directorate Identifier 2009–SW–43–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 notice and 

prior public comment are unnecessary 

in promulgating this regulation; 

therefore, it can be issued immediately 

to correct an unsafe condition in aircraft 

since none of these model helicopters 

are registered in the United States. We 

have also determined that this 

regulation is not a ‘‘significant 

regulatory action’’ under Executive 

Order 12866. It has been determined 

further that this action involves an 

emergency regulation under DOT 

Regulatory Policies and Procedures (44 

FR 11034, February 26, 1979). If it is 

determined that this emergency 

regulation otherwise would be 

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66620 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

significant under DOT Regulatory 

Policies and Procedures, a final 

regulatory evaluation will be prepared 

and placed in the AD docket. 

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: 

2011–20–05 Eurocopter France 

(Eurocopter): Amendment 39–16815; 

Docket No. FAA–2011–1033; Directorate 

Identifier 2009–SW–43–AD. 

Applicability: Model EC225LP helicopters, 

certificated in any category, that have not 

been modified in accordance with Eurocopter 

Modification (MOD) 0743718. 

Compliance: Required as indicated. 

To prevent loss of the dome fairing in 

flight, damage to the helicopter, and injury to 

people on the ground, accomplish the 

following: 

(a) Within 15 hours time-in-service (TIS), 

unless accomplished previously, inspect for 

a crack in the dome fairing support at the 

dome fairing attachment points. 

(1) If a crack is found in the dome fairing 

support or at a dome fairing attachment 

point, before further flight, replace the dome 

fairing support and the associated coning 

stop support assembly. 

(2) If no crack is found, thereafter at 

intervals not exceeding 165 hours TIS, 

inspect for a crack in the dome fairing 

support, and re-torque the screws securing 

the dome fairing support to the dome fairing. 

Note 1: Eurocopter Emergency Alert 

Service Bulletin No. 05A005, Revision 1, 

dated February 3, 2009, and Service Bulletin 

No. 62–007, Revision 1, dated July 10, 2009, 

which are not incorporated by reference, 

contain additional information about the 

subject of this AD. 

(b) Accomplishing Eurocopter MOD 

0743718 constitutes terminating action for 

the requirements of this AD. 

(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, FAA, Attn: Gary Roach, 

Aviation Safety Engineer, FAA, Regulations 

and Policy Group, 2601 Meacham Blvd., Fort 

Worth, Texas 76137; telephone: (817) 222– 

5130; fax: 817–222–5961, for information 

about previously approved alternative 

methods of compliance. 

(d) A special flight permit will not be 

issued. 

(e) The Joint Aircraft System/Component 

(JASC) Code is 6300: Main Rotor Drive 

System. 

(f) This amendment becomes effective on 

November 14, 2011. 

Note 2: The subject of this AD is addressed 

in European Aviation Safety Agency AD No. 

2009–0023, dated February 20, 2009. 

Issued in Fort Worth, Texas, on September 

13, 2011. 

Lance T. Gant, 

Acting Manager, Rotorcraft Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27771 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–1096; Directorate 

Identifier 2011–NM–185–AD; Amendment 

39–16848; AD 2011–22–06] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–215–1A10, CL–215– 

6B11 (CL–215T Variant), and CL–215– 

6B11 (CL–415 Variant) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; request for 

comments. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Bombardier, Inc. Model CL–215–1A10, 

CL–215–6B11 (CL–215T Variant), and 

CL–215–6B11 (CL–415 Variant) 

airplanes. 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 MCAI 

describes the unsafe condition as: 

Multiple cracks were reported on the Main 

Landing Gear (MLG) upper member forward 

lug, part numbers 160–714–3 (L/H) and 160– 

714–4 (R/H). An investigation determined the 

cause to be fatigue cracks at the base of the 

step radius with multiple initiation sites. The 

fatigue cracking may compromise the 

structural integrity of the MLG during takeoff 

or landing, leading to failure. 

* * * * * 

This AD requires actions that are 

intended to address the unsafe 

condition described in the MCAI. 

DATES: This AD becomes effective 

November 14, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in the AD 

as of November 14, 2011. 

We must receive comments on this 

AD by December 12, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• 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, between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

Examining the AD Docket 

You may examine the AD docket 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 AD docket 

contains this AD, the regulatory 

evaluation, any comments received, and 

other information. The street address for 

the Docket Operations office (telephone 

(800) 647–5527) is in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: Aziz 

Ahmed, Aerospace Engineer, Airframe 

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