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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Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 66621 

and Mechanical Systems Branch, ANE– 

171, FAA, New York Aircraft 

Certification Office, 1600 Stewart 

Avenue, Suite 410, Westbury, New York 

11590; telephone (516) 228–7329; fax 

(516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

Transport Canada Civil Aviation 

(TCCA), which is the aviation authority 

for Canada, has issued Canadian 

Airworthiness Directive CF–2011–35, 

dated August 29, 2011 (referred to after 

this as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

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 [Canadian] directive mandates 

repetitive eddy current inspections and a 

one-time fluorescent penetrant inspection of 

the MLG upper member forward lugs to 

determine fleet condition. Pending fleet 

inspection results, further action may result 

to mitigate the risk of failure due to fatigue 

cracks. 

The action includes inspecting for any 

cracks. The corrective action is 

replacing the forward lug of the MLG 

upper member with a new forward lug 

if any crack is found. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Alert Service 

Bulletin 215–A548, dated July 15, 2011; 

Alert Service Bulletin 215–A4451, dated 

July 15, 2011; Alert Service Bulletin 

215–A547, dated July 8, 2011; and Alert 

Service Bulletin 215–A4450, dated July 

8, 2011. The actions described in this 

service information are intended to 

correct the unsafe condition identified 

in the MCAI. 

FAA’s Determination and Requirements 

of This AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are issuing this 

AD because we evaluated all pertinent 

information and determined the unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Differences Between the 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. 

FAA’s Determination of the Effective 

Date 

An unsafe condition exists that 

requires the immediate adoption of this 

AD. The FAA has found that the risk to 

the flying public justifies waiving notice 

and comment prior to adoption of this 

rule because multiple cracks were 

reported on the forward lug of the upper 

member of the MLG. An investigation 

determined the cause to be fatigue 

cracking at the base of the step radium 

with multiple initiation sites. The 

fatigue cracking could adversely affect 

the structural integrity of the MLG 

during takeoff or landing. Therefore, we 

determined that notice and opportunity 

for public comment before issuing this 

AD are impracticable and that good 

cause exists for making this amendment 

effective in fewer than 30 days. 

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 section. 

Include ‘‘Docket No. FAA–2011–1096; 

Directorate Identifier 2011–NM–185– 

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 we receive 

about this AD. 

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 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 a regulatory 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. 

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66622 Federal Register / Vol. 76, No. 208 / Thursday, October 27, 2011 / Rules and Regulations 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–22–06 Bombardier, Inc.: Amendment 

39–16848. Docket No. FAA–2011–1096; 

Directorate Identifier 2011–NM–185–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective November 14, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc., 

airplanes, certificated in any category, 

identified in paragraphs (c)(1), (c)(2), and 

(c)(3) of this AD. 

(1) Model CL–215–1A10 airplanes, serial 

numbers 1051 through 1125 inclusive; 

(2) Model CL–215–6B11 (CL–215T Variant) 

airplanes, serial numbers 1056 through 1125 

inclusive; and 

(3) Model CL–215–6B11 (CL–415 Variant) 

airplanes, serial numbers 2001 through 2990 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

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. 

* * * * * 

Compliance 

(f) You are responsible for having the 

actions required by this AD performed within 

the compliance times specified, unless the 

actions have already been done. 

Eddy Current Inspections 

(g) Within 50 flight hours after the effective 

date of this AD: Perform an in situ eddy 

current inspection for cracks on the forward 

lug of the MLG upper member, part numbers 

160–714–3 (left hand) and 160–714–4 (right 

hand), in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A548, dated July 

15, 2011 (for Model CL–215–1A10 airplanes, 

and Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4451, dated July 15, 2011 (for 

Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

(1) If any crack is found: Before further 

flight, replace the forward lug of the MLG 

upper member with a new forward lug, in 

accordance with the Accomplishment 

Instructions of Bombardier Alert Service 

Bulletin 215–A548, dated July 15, 2011 (for 

Model CL–215–1A10 airplanes, and Model 

CL–215–6B11 (CL–215T Variant) airplanes); 

or Bombardier Alert Service Bulletin 215– 

A4451, dated July 15, 2011 (for Model CL– 

215–6B11 (CL–415 Variant) airplanes). 

Thereafter, repeat the in situ eddy current 

inspection at intervals not to exceed 165 land 

landings. 

(2) If no crack is found: Repeat the in situ 

eddy current inspection at intervals not to 

exceed 165 land landings, in accordance with 

the Accomplishment Instructions of 

Bombardier Alert Service Bulletin 215–A548, 

dated July 15, 2011 (for Model CL–215–1A10 

airplanes, and Model CL–215–6B11 (CL– 

215T Variant) airplanes); or Bombardier Alert 

Service Bulletin 215–A4451, dated July 15, 

2011 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). 

Fluorescent Penetrant Inspection 

(h) Within two months after the effective 

date of this AD: Perform a one-time 

fluorescent penetrant inspection for cracks 

on the forward lug of the MLG upper 

member, part numbers 160–714–3 (left hand) 

and 160–714–4 (right hand), in accordance 

with the Accomplishment Instructions of 

Bombardier Alert Service Bulletin 215–A547, 

dated July 8, 2011 (for Model CL–215–1A10 

airplanes, and Model CL–215–6B11 (CL– 

215T Variant) airplanes); or Bombardier Alert 

Service Bulletin 215–A4450, dated July 8, 

2011 (for Model CL–215–6B11 (CL–415 

Variant) airplanes). If any crack is found, 

before further flight, replace the forward lug 

of the MLG upper member with a new 

forward lug, in accordance with the 

Accomplishment Instructions of Bombardier 

Alert Service Bulletin 215–A547, dated July 

8, 2011 (for Model CL–215–1A10 airplanes, 

and Model CL–215–6B11 (CL–215T Variant) 

airplanes); or Bombardier Alert Service 

Bulletin 215–A4450, dated July 8, 2011 (for 

Model CL–215–6B11 (CL–415 Variant) 

airplanes). 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: 

If any cracking is found during any in situ 

eddy current inspection specified in 

paragraph (g) of this AD, and the forward lug 

of the MLG upper member is replaced, this 

AD requires repetitive in situ eddy current 

inspections, thereafter, at intervals not to 

exceed 165 land landings. Canadian 

Airworthiness Directive CF–2011–35, dated 

August 29, 2011, does not include this 

requirement. 

Other FAA AD Provisions 

(i) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office (ACO), ANE–170, FAA, 

has the authority to approve AMOCs for this 

AD, if requested using the procedures found 

in 14 CFR 39.19. In accordance with 14 CFR 

39.19, send your request to your principal 

inspector or local Flight Standards District 

Office, as appropriate. If sending information 

directly to the New York ACO, send it to 

Attn: Program Manager, Continuing 

Operational Safety, FAA, New York ACO, 

1600 Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone 516–228–7300; 

fax 516–794–5531. Before using any 

approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(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. 

(j) Special Flight Permits: Special flight 

permits, as described in Section 21.197 and 

Section 21.199 of the Federal Aviation 

Regulations (14 CFR 21.197 and 21.199), are 

not allowed. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2011–35, dated August 29 2011; 

Bombardier Alert Service Bulletin 215–A548, 

dated July 15, 2011; Bombardier Alert 

Service Bulletin 215–A4451, dated July 15, 

2011; Bombardier Alert Service Bulletin 215– 

A547, dated July 8, 2011; and Bombardier 

Alert Service Bulletin 215–A4450, dated July 

8, 2011; for related information. 

Material Incorporated by Reference 

(l) You must use Bombardier Alert Service 

Bulletin 215–A548, dated July 15, 2011; 

Bombardier Alert Service Bulletin 215– 

A4451, dated July 15, 2011; Bombardier Alert 

Service Bulletin 215–A547, dated July 8, 

2011; and Bombardier Alert Service Bulletin 

215–A4450, dated July 8, 2011; 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 Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que ́bec H4S 1Y9, 

Canada; telephone 514–855–5000; fax 514– 

855–7401; e-mail 

thd.crj@aero.bombardier.com; Internet http:// 

www.bombardier.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 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 October 

13, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–27599 Filed 10–26–11; 8:45 am] 

BILLING CODE 4910–13–P 

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