33984 Federal Register / Vol. 76, No. 112 / Friday, June 10, 2011 / Rules and Regulations 

Subject 

(d) Air Transport Association (ATA) of 

America Code 27: Flight controls. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

An inspection by the vendor revealed that 

a number of Rubber Bull Gears (RBG) in the 

Horizontal Stabilizer Trim Actuator (HSTA) 

of the CL–600–2C10, CL–600–2D15 and CL– 

600–2D24 aeroplanes were installed with a 

wheel material hardness out of specification. 

This non-conformity has a direct impact on 

the HSTA life limit. The teeth of these nonconformant RBGs could break and in extreme 

cases, could lead to uncontrolled HSTA 

movement without the ability to re-trim the 

aeroplane. If not corrected, this condition 

could result in a difficulty to control the 

pitch and subsequent loss of the aeroplane. 

* * * * * 

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. 

Modifying the HSTA 

(g) For airplanes having any HSTA with 

S/N 107, 111, 124, 126, 135, 139, 142, 145, 

146, 266, 268, 271, 274, 276, 277, 280, 282 

through 285 inclusive, 290, 292, 294, 297, 

299, 307, 309, 320, 337, 400, 402, 403, 410, 

412, 418, 421 through 428 inclusive, 430, 435 

through 439 inclusive, 441, 443 through 446 

inclusive, 448 through 450 inclusive, 452 

through 454 inclusive, 456, 459, 461, 463 

through 470 inclusive, 472, 474 through 476 

inclusive, 478, 545 through 549 inclusive, 

570, 571, 573, 574, 600, 603, 608, 612 

through 616 inclusive, 623, 627, and 629 

through 659 inclusive: At the applicable 

compliance time specified in paragraph (g)(1) 

or (g)(2) of this AD, replace the HSTA with 

a modified HSTA, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–27–058, dated 

August 31, 2010. 

(1) For HSTAs that have accumulated 

8,700 total flight cycles or less as of the 

effective date of this AD: Within 3,000 flight 

cycles from the effective date of this AD, or 

before the HSTA has accumulated 10,500 

flight cycles, whichever occurs first. 

(2) For HSTAs that have accumulated more 

than 8,700 total flight cycles as of the 

effective date of this AD: Within 1,800 flight 

cycles after the effective date of this AD. 

(h) For airplanes having any HSTA with S/ 

N 185, 479, 481, 482, 485, 487, 489, 491 

through 496 inclusive, 498, 499, 501, 503, 

504, 506, 507, 509, 512 through 514 

inclusive, 517, 519 through 522 inclusive, 

524, 526 through 528 inclusive, 530, 534 

through 536 inclusive, 539, 542, and 543: 

Within 1,800 flight cycles after the effective 

date of this AD, replace the affected HSTA 

with a modified HSTA in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–27–058, 

dated August 31, 2010. 

Parts Installation 

(i) As of the effective date of this AD, no 

person may install a HSTA, having P/N 

8489–5, 8489–6, 8489–7, or 8489–7R, with 

any serial numbers identified in paragraph 

(g) or (h) of this AD, on any airplane, unless 

that HSTA has been modified in accordance 

with SAGEM Service Bulletin 8489–27–007, 

Revision 1, dated August 10, 2010, and that 

HSTA has a suffix ‘‘B’’ beside the serial 

number. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(j) The following provisions also apply to 

this AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, New York Aircraft 

Certification Office, 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. Send information 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. 

Related Information 

(k) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–34, dated October 5, 

2010; Bombardier Service Bulletin 670BA– 

27–058, dated August 31, 2010; and SAGEM 

Service Bulletin 8489–27–007, Revision 1, 

dated August 10, 2010; for related 

information. 

Material Incorporated by Reference 

(l) You must use Bombardier Service 

Bulletin 670BA–27–058, dated August 31, 

2010; and SAGEM Service Bulletin 8489–27– 

007, Revision 1, dated August 10, 2010; 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 May 20, 

2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–13650 Filed 6–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0456; Directorate 

Identifier 2011–NE–15–AD; Amendment 39– 

16711; AD 2011–12–04] 

RIN 2120–AA64 

Airworthiness Directives; BRP– 

Powertrain GmbH & Co. KG Rotax 912 

F3, 912 S2, 912 S3, 912 S4, 914 F2, 914 

F3, and 914 F4 Reciprocating Engines 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule; request for 

comments. 

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: 

During a production process review, a 

deviation in hardening of certain Part 

Number (P/N) 944072 washers has been 

detected, which exceeds the hardness of the 

design specification. 

The affected washers are part of the 

magneto ring flywheel hub installation and 

have been installed on a limited number of 

engines. No defective washers have been 

shipped as spare parts. 

This condition, if not corrected, could lead 

to cracks in the washer, loosening of the 

magneto flywheel hub and consequent 

ignition failure, possibly resulting in damage 

to the engine, in-flight engine shutdown and 

forced landing, damage to the aeroplane and 

injury to occupants. 

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Federal Register / Vol. 76, No. 112 / Friday, June 10, 2011 / Rules and Regulations 33985 

We are issuing this AD to prevent 

engine in-flight shutdown, and damage 

to the airplane. 

DATES: This AD becomes effective June 

27, 2011. 

We must receive comments on this 

AD by July 11, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of BRP–Powertrain GmbH & Co. KG 

Rotax Mandatory Service Bulletins No. 

SB–912–058 and No. SB–914–041 

(combined in one document), dated 

April 15, 2011, listed in the AD as of 

June 27, 2011. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov and follow 

the instructions for sending your 

comments electronically. 

• Mail: U.S. Department of 

Transportation, 1200 New Jersey 

Avenue, SE., West Building Ground 

Floor, Room W12–140, Washington, DC 

20590–0001. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

• Fax: (202) 493–2251. 

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 (phone: 

(800) 647–5527) is the same as the Mail 

address provided in the ADDRESSES

section. Comments will be available in 

the AD docket shortly after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Strom, Aerospace Engineer, Engine 

Certification Office, FAA, Engine & 

Propeller Directorate, 12 New England 

Executive Park, Burlington, MA 01803; 

e-mail: alan.strom@faa.gov; phone: 

(781) 238–7143; fax: (781) 238–7199. 

SUPPLEMENTARY INFORMATION: 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0067–E, 

dated April 15, 2011 (referred to after 

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

condition for the specified products. 

The MCAI states: 

During a production process review, a 

deviation in hardening of certain Part 

Number (P/N) 944072 washers has been 

detected, which exceeds the hardness of the 

design specification. 

The affected washers are part of the 

magneto ring flywheel hub installation and 

have been installed on a limited number of 

engines. No defective washers have been 

shipped as spare parts. 

This condition, if not corrected, could lead 

to cracks in the washer, loosening of the 

magneto flywheel hub and consequent 

ignition failure, possibly resulting in damage 

to the engine, in-flight engine shutdown and 

forced landing, damage to the aeroplane and 

injury to occupants. 

You may obtain further information 

by examining the MCAI in the AD 

docket. 

Relevant Service Information 

BRP–Powertrain GmbH & Co. KG has 

issued Rotax Mandatory Service 

Bulletins No. SB–912–058 and No. SB– 

914–041 (combined in one document), 

dated April 15, 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 Austria and is 

approved for operation in the United 

States. Pursuant to our bilateral 

agreement with Austria, EASA has 

notified us of the unsafe condition 

described in the MCAI and service 

information referenced above. We are 

issuing this AD because we evaluated 

all information provided by EASA and 

determined the unsafe condition exists 

and is likely to exist or develop on other 

products of the same type design. This 

AD requires replacing the washer 

securing the magneto ring flywheel hub 

with a new washer of the same part 

number, on certain serial number BRP– 

Powertrain GmbH & Co. KG Rotax 912 

and 914 reciprocating engines. 

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 of the short compliance 

time in this AD of within 10 flight hours 

or at next maintenance after the 

effective date of the AD, whichever 

occurs first. 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–2011–0456; 

Directorate Identifier 2011–NE–15–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 Web site, anyone 

can find and read the comments in any 

of our dockets, including, if provided, 

the name of the individual who sent the 

comment (or signed the comment on 

behalf of an association, business, labor 

union, etc.). You may review the DOT’s 

complete Privacy Act Statement in the 

Federal Register published on April 11, 

2000 (65 FR 19477–78). 

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 

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33986 Federal Register / Vol. 76, No. 112 / Friday, June 10, 2011 / Rules and Regulations 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by adding 

the following new AD: 

2011–12–04 BRP–Powertrain GmbH & Co. 

KG (Formerly Bombardier-Rotax 

GmbH): Amendment 39–16711.; Docket 

No. FAA–2011–0456; Directorate 

Identifier 2011–NE–15–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective June 27, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the following BRP– 

Powertrain GmbH & Co. KG Rotax 

reciprocating engines: 

(1) Model 912 F3—serial number (S/N) 

4,412.986 and S/N 4,412.987. 

(2) Models 912 S2, 912 S3, and 912 S4— 

S/N 4,924.087 through S/N 4,924.139 

inclusive, and S/N 4,924.141 through 

4,924.166 inclusive. 

(3) Models 914 F2, 914 F3, and 914 F4— 

S/N 4,420.970 through 4,420.990 inclusive, 

S/N 4,420.997, and S/N 4,421.001 through 

4,421.003 inclusive. 

Reason 

(d) 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: 

During a production process review, a 

deviation in hardening of certain Part 

Number (P/N) 944072 washers has been 

detected, which exceeds the hardness of the 

design specification. 

The affected washers are part of the 

magneto ring flywheel hub installation and 

have been installed on a limited number of 

engines. No defective washers have been 

shipped as spare parts. 

This condition, if not corrected, could lead 

to cracks in the washer, loosening of the 

magneto flywheel hub and consequent 

ignition failure, possibly resulting in damage 

to the engine, in-flight engine shutdown and 

forced landing, damage to the aeroplane and 

injury to occupants. 

We are issuing this AD to prevent engine 

in-flight shutdown, and damage to the 

airplane. 

Actions and Compliance 

(e) Unless already done, do the following 

actions within 10 flight hours or at next 

maintenance after the effective date of this 

AD, whichever occurs first: 

(1) Replace the magneto ring flywheel hub 

washer, P/N 944072. 

(2) Use paragraph 3.1 of BRP–Powertrain 

GmbH & Co. KG Rotax Mandatory Service 

Bulletin SB–912–058, dated April 15, 2011 or 

SB–914–041 dated April 15, 2011, to do the 

replacement. 

Prohibition 

(f) After the effective date of this AD, do 

not install any washer P/N 944072 removed 

as specified in paragraph (e)(1) of this AD 

into any magneto or onto any engine. 

FAA AD Differences 

(g) This AD differs from the Mandatory 

Continuing Airworthiness Information 

(MCAI) as follows: 

(1) European Aviation Safety Agency 

(EASA) AD 2011–0067–E requires 

compliance within 10 flight hours or 4 

calendar months after the effective date of the 

AD, whichever occurs first. This AD requires 

compliance within 10 flight hours or at next 

maintenance after the effective date of this 

AD, whichever occurs first. 

(2) EASA AD 2011–0067–E requires 

operators to return the washer removed from 

service to BRP–Powertrain GmbH & Co. KG. 

This AD does not. 

Alternative Methods of Compliance 

(AMOCs) 

(h) The Manager, Engine Certification 

Office, FAA, has the authority to approve 

AMOCs for this AD, if requested using the 

procedures found in 14 CFR 39.19. 

Related Information 

(i) Refer to MCAI EASA AD 2011–0067–E, 

dated April 15, 2011, for related information. 

(j) Contact Alan Strom, Aerospace 

Engineer, Engine Certification Office, FAA, 

Engine & Propeller Directorate, 12 New 

England Executive Park, Burlington, MA 

01803; e-mail: alan.strom@faa.gov; phone 

(781) 238–7143; fax (781) 238–719, for more 

information about this AD. 

Material Incorporated by Reference 

(k) You must use BRP–Powertrain GmbH & 

Co. KG Rotax Mandatory Service Bulletins 

No. SB–912–058 and No. SB–914–041 

(combined in one document), dated April 15, 

2011, to do the actions required by this AD. 

(1) For service information identified in 

this AD, contact BRP–Powertrain GmbH & 

Co. KG, Welser Strasse 32, A–4623 

Gunskirchen, Austria, or go to: http:// 

www.rotax-aircraft-engines.com. 

(2) You may review copies at the FAA, 

New England Region, 12 New England 

Executive Park, Burlington, MA; 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/ibrlocations.html. 

Issued in Burlington, Massachusetts, on 

May 26, 2011. 

Peter A. White, 

Acting Manager, Engine and Propeller 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–14239 Filed 6–9–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–1277; Directorate 

Identifier 2010–NM–218–AD; Amendment 

39–16722; AD 2009–18–19 R1] 

RIN 2120–AA64 

Airworthiness Directives; Airbus Model 

A330–200 and –300 Series Airplanes, 

and Model A340–200 and –300 Series 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule; rescission. 

SUMMARY: This amendment rescinds 

airworthiness directive (AD) 2009–18– 

19 for the products listed above. This 

AD results from mandatory continuing 

airworthiness information (MCAI) 

issued by EASA, to rescind EASA AD 

2010–0083. The MCAI specifies the 

following: 

It has been assessed that multiple NRV 

[non-return valve] failures in combination 

with certain trapped fuel cases could 

potentially increase the quantity of unusable 

fuel on the aeroplane, possibly leading to fuel 

starvation which could result in engines inflight shut down and would constitute an 

unsafe condition. To prevent and detect this 

condition, EASA issued EASA AD 2010– 

0083. 

Based on in service experience, mainly on 

the results of the operational test required by 

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