Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 42033 

Dornier GmbH; Dornier Luftfahrt GmbH) 

Model 328–100 and –300 airplanes, 

certificated in any category, all serial 

numbers. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 55: Stabilizers. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

During maintenance, it has been 

discovered that at the installation of the 

fixation brackets for rudder spring tabs and 

trim tabs an incorrect installation of the 

fixation brackets may have occurred. * * * 

If the orientation of the fixation bracket is 

reversed or upside down the screws may not 

reach into the helicoil thread to a sufficient 

depth. 

An incorrect installation, if not detected 

and corrected, could lead to an in-flight 

failure of the fixation brackets for rudder 

spring tabs and trim tabs resulting in and 

reduced control 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. 

Inspection 

(g) Within 400 flight hours after the 

effective date of this AD, do a detailed 

inspection to determine if the fixation 

brackets for the rudder spring tabs and trim 

tabs are installed correctly, in accordance 

with the Accomplishment Instructions of 328 

Support Services Service Bulletin SB–328– 

55–493, dated April 21, 2010 (for Model 328– 

100 airplanes); or SB–328J–55–245, dated 

April 21, 2010 (for Model 328–300 airplanes). 

Corrective Action 

(h) If, during the inspection required by 

paragraph (g) of this AD, any incorrect 

installation of the fixation brackets for rudder 

spring tabs and trim tabs is detected, before 

further flight, correct the installation of the 

fixation brackets for rudder spring tabs and 

trim tabs, in accordance with the 

Accomplishment Instructions of 328 Support 

Services Service Bulletin SB–328–55–493, 

dated April 21, 2010 (for Model 328–100 

airplanes); or SB–328J–55–245, dated April 

21, 2010 (for Model 328–300 airplanes). 

Reporting 

(i) Within 30 days after the inspection 

required by paragraph (g) of this AD, or 

within 30 days after the effective date of this 

AD, whichever occurs later: Send the 

inspection report to 328 Support Services 

GmbH by using the Compliance Report 

attached to 328 Support Services Service 

Bulletin SB–328–55–493, dated April 21, 

2010 (for Model 328–100 airplanes); or SB– 

328J–55–245, dated April 21, 2010 (for Model 

328–300 airplanes). Send the report by mail 

or fax to: Attention: Dept. C, 328 Support 

Services GmbH, Customer Services, P.O. Box 

1252, D–82231 Wessling, Federal Republic of 

Germany; fax +49 (0) 8153 88111–6565. 

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, International 

Branch, ANM–116, Transport Airplane 

Directorate, 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 International Branch, send it to ATTN: 

Tom Rodriguez, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 227–1137; fax (425) 

227–1149. Information may be e-mailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

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. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave., SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

Related Information 

(k) Refer to MCAI European Aviation 

Safety Agency (EASA) Airworthiness 

Directive 2010–0134, dated June 30, 2010; 

and 328 Support Services Service Bulletins 

SB–328–55–493 and SB–328J–55–245, both 

dated April 21, 2010; for related information. 

Material Incorporated by Reference 

(l) You must use 328 Support Services 

Service Bulletin SB–328–55–493, dated April 

21, 2010, including Compliance Report; or 

328 Support Services Service Bulletin SB– 

328J–55–245, dated April 21, 2010, including 

Compliance Report; as applicable; to do the 

actions required by this AD, unless the AD 

specifies otherwise. Only the even pages of 

these documents include the document date. 

The compliance reports attached to these 

documents do not contain document 

numbers, revision levels, or dates. 

(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 328 Support Services GmbH, 

Global Support Center, P.O. Box 1252, 

D–82231 Wessling, Federal Republic of 

Germany; telephone +49 8153 88111 6666; 

fax +49 8153 88111 6565; e-mail 

gsc.op@328support.de; Internet http:// 

www.328support.de. 

(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 July 6, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17703 Filed 7–15–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2011–0718; Directorate 

Identifier 2011–NM–117–AD; Amendment 

39–16756; AD 2011–15–09] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model DHC–8–400 Series 

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 the 

products listed above that would 

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42034 Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 

supersede an existing AD. 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: 

Two cases of the main landing gear (MLG) 

alternate extension system (AES) cam 

mechanism failure were found during line 

checks. The cam mechanism operates the 

cable to open the MLG door and releases the 

MLG uplock in sequence. In the case where 

it is necessary to deploy the MLG using the 

AES, the failure of the MLG AES cam 

mechanism on one side will lead to an unsafe 

asymmetrical landing configuration. 

* * * * * 

The unsafe condition is possible loss 

of control during landing. This AD 

requires actions that are intended to 

address the unsafe condition described 

in the MCAI. 

DATES: This AD becomes effective 

August 2, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of August 2, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain other publication listed in 

the AD as of March 25, 2011 (76 FR 

13080, March 10, 2011). 

We must receive comments on this 

AD by September 1, 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 

W12–40, 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: 

Cesar Gomez, Aerospace Engineer, 

Airframe and Mechanical Systems 

Branch, ANE–171, FAA, New York 

Aircraft Certification Office, 1600 

Stewart Avenue, Suite 410, Westbury, 

New York 11590; telephone (516) 228– 

7318; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

On February 22, 2011, we issued AD 

2011–05–14, Amendment 39–16624 (76 

FR 13080, March 10, 2011). That AD 

required actions intended to address an 

unsafe condition on the products listed 

above. 

Since we issued AD 2011–05–14, we 

have received a report that the service 

information referenced in that AD as a 

source of accomplishment information 

was found to have inadequate 

inspection procedures. Transport 

Canada Civil Aviation (TCCA), which is 

the aviation authority for Canada, has 

issued Canadian Airworthiness 

Directive CF–2011–01R1, dated May 20, 

2011 (referred to after this as ‘‘the 

MCAI’’), to correct an unsafe condition 

for the specified products. The MCAI 

states: 

Two cases of the main landing gear (MLG) 

alternate extension system (AES) cam 

mechanism failure were found during line 

checks. The cam mechanism operates the 

cable to open the MLG door and releases the 

MLG uplock in sequence. In the case where 

it is necessary to deploy the MLG using the 

AES, the failure of the MLG AES cam 

mechanism on one side will lead to an unsafe 

asymmetrical landing configuration. 

Preliminary investigation indicates that the 

cam mechanism failure may have occurred 

and remained dormant after a previous AES 

operation. The cam mechanism may not have 

fully returned to the normal rested position. 

With the cam mechanism out of normal 

rested position, normal powered landing gear 

door operation could introduce sufficient 

loads to fracture the cam mechanism or 

rupture the door release cable. 

This directive mandates the initial and 

subsequent [detailed] inspections for proper 

operation of the MLG AES cam mechanism, 

and rectify [repair or replace cam assembly 

with new or serviceable cam assembly] as 

necessary. 

Since the original issue of this [Canadian] 

directive, Bombardier Inc. has determined 

that the existing inspection procedure is 

insufficient for verification of proper MLG 

AES cam mechanism operation, and has 

superseded this inspection procedure. This 

revision of the [Canadian] directive mandates 

the use of the latest inspection [and 

rectification] procedure. 

The unsafe condition is possible loss of 

control during landing. You may obtain 

further information by examining the 

MCAI in the AD docket. 

Relevant Service Information 

Bombardier has issued Repair 

Drawing 8/4–32–0160, Issue 3, dated 

February 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 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 since we issued AD 

2011–05–14, Bombardier has 

determined that the existing inspection 

procedure referenced in AD 2011–05–14 

is insufficient for verification of proper 

MLG AES cam mechanism operation, 

and has provided a revised inspection 

procedure. In the case where it is 

necessary to deploy the MLG using the 

AES, the failure of the MLG AES cam 

mechanism on one side will lead to an 

unsafe asymmetrical landing 

configuration. An asymmetrical landing 

configuration could result in possible 

loss of control during landing. This AD 

mandates the use of the revised 

inspection procedures. Therefore, we 

determined that notice and opportunity 

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Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 42035 

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–2011–0718; 

Directorate Identifier 2011–NM–117– 

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. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Amendment 39–16624 

(76 FR 13080, March 10, 2011) and 

adding the following new AD: 

2011–15–09 Bombardier, Inc.: Amendment 

39–16756. Docket No. FAA–2011–0718; 

Directorate Identifier 2011–NM–117–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective August 2, 2011. 

Affected ADs 

(b) This AD supersedes AD 2011–05–14, 

Amendment 39–16624. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model DHC–8–400, –401, and –402 

airplanes, certificated in any category, serial 

numbers 4001 and subsequent. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 32: Landing Gear. 

Reason 

(e) The mandatory continued airworthiness 

information (MCAI) states: 

Two cases of the main landing gear (MLG) 

alternate extension system (AES) cam 

mechanism failure were found during line 

checks. The cam mechanism operates the 

cable to open the MLG door and releases the 

MLG uplock in sequence. In the case where 

it is necessary to deploy the MLG using the 

AES, the failure of the MLG AES cam 

mechanism on one side will lead to an unsafe 

asymmetrical landing configuration. 

* * * * * 

The unsafe condition is possible loss of 

control during landing. 

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. 

Restatement of Requirements of AD 2011– 

05–14, With New Service Information 

(g) Within 50 flight hours or 10 days after 

March 25, 2011 (the effective date of AD 

2011–05–14), whichever occurs first, do a 

detailed inspection for proper operation of 

the MLG AES cam mechanism, in accordance 

with paragraph A) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 2, dated January 

18, 2011; or Issue 3, dated February 15, 2011. 

Repeat the inspection thereafter at intervals 

not to exceed 50 flight hours or 10 days, 

whichever occurs first, until the inspection 

required by paragraph (i) of this AD is 

accomplished. 

(1) If the cam mechanism is found to reset 

to the normal rested position without any 

sticking or binding, it is operating properly. 

(2) If the cam mechanism has not reset to 

its normal rested position, or if any sticking 

or binding is observed, before further flight, 

remove the cam assembly, in accordance 

with paragraph A) of Bombardier Repair 

Drawing 8/4–32–0160, Issue 2, dated January 

18, 2011; or Issue 3, dated February 15, 2011; 

and do the actions in paragraph (g)(2)(i) or 

(g)(2)(ii) of this AD. 

(i) Repair the cam mechanism assembly, 

including doing detailed inspections for 

discrepancies (including an inspection to 

determine proper operation, an inspection for 

damage, an inspection for corrosion and 

cadmium coating degradation, and 

inspections to determine dimensions are 

within the limits specified in paragraph B) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 2, dated January 18, 2011; or Issue 3, 

dated February 15, 2011), in accordance with 

paragraph B) of Bombardier Repair Drawing 

8/4–32–0160, Issue 2, dated January 18, 2011; 

or Issue 3, dated February 15, 2011; and 

install the repaired cam assembly in 

accordance with paragraph C) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 2, dated 

January 18, 2011; or Issue 3, dated February 

15, 2011. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 2, dated January 18, 2011; or Issue 3, 

dated February 15, 2011. 

(3) If the cam mechanism is found 

damaged or inoperative during the repair 

specified in paragraph (g)(2)(i) of this AD, or 

if any discrepancies are found and 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 2, dated January 18, 2011; or Issue 3, 

dated February 15, 2011; does not specify 

repairs for those discrepancies, or repairs 

specified in paragraph (g)(2)(i) of this AD 

cannot be accomplished: Before further 

flight, repair and reinstall using a method 

approved by the Manager, ANE–170, New 

York Aircraft Certification Office (ACO), 

FAA, or Transport Canada Civil Aviation 

(TCCA) (or its delegated agent); or install a 

new or serviceable cam assembly, in 

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42036 Federal Register / Vol. 76, No. 137 / Monday, July 18, 2011 / Rules and Regulations 

accordance with paragraph C) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 2, dated 

January 18, 2011; or Issue 3, dated February 

15, 2011. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions done before March 25, 2011, in 

accordance with Bombardier 8/4–32–0160, 

Issue 1, dated January 14, 2011, are 

acceptable for compliance with the 

corresponding requirements of this AD. 

New Requirements of This AD 

(i) Within 50 flight hours or 10 days after 

the effective date of this AD, whichever 

occurs first, do a detailed inspection for 

proper operation of the MLG AES cam 

mechanism, in accordance with paragraph A) 

of Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011. Repeat the 

inspection thereafter at intervals not to 

exceed 50 flight hours or 10 days, whichever 

occurs first. Accomplishing this inspection 

terminates the requirements of paragraph (g) 

of this AD. 

(1) If the cam mechanism is found to reset 

to the normal rested position without any 

sticking or binding, it is operating properly. 

(2) If the cam mechanism has not reset to 

its normal rested position, or if any sticking 

or binding is observed, before further flight, 

remove the cam assembly, in accordance 

with paragraph A) of Bombardier Repair 

Drawing 

8/4–32–0160, Issue 3, dated February 15, 

2011, and do the actions in paragraph (i)(2)(i) 

or (i)(2)(ii) of this AD. 

(i) Repair the cam mechanism assembly, 

including doing detailed inspections for 

discrepancies (including an inspection to 

determine proper operation, an inspection for 

damage, an inspection for corrosion and 

cadmium coating degradation, and 

inspections to determine dimensions are 

within the limits specified in paragraph B) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011), in 

accordance with paragraph B) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011; and install the repaired 

cam assembly in accordance with paragraph 

C) of Bombardier Repair Drawing 8/4–32– 

0160, Issue 3, dated February 15, 2011. 

(ii) Install a new or serviceable cam 

assembly, in accordance with paragraph C) of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011. 

(3) If the cam mechanism is found 

damaged or inoperative during the repair 

specified in paragraph (i)(2)(i) of this AD, or 

if any discrepancies are found and 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011, does not 

specify repairs for those discrepancies, or 

repairs specified in paragraph (i)(2)(i) of this 

AD cannot be accomplished: Before further 

flight, repair and reinstall using a method 

approved by the Manager, ANE–170, New 

York Aircraft Certification Office (ACO), 

FAA, or Transport Canada Civil Aviation 

(TCCA) (or its delegated agent); or install a 

new or serviceable cam assembly, in 

accordance with paragraph C) of Bombardier 

Repair Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011. 

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, ANE–170, New York 

ACO, 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 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 FAAapproved 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–2011–01R1, dated May 20, 

2011; Bombardier Repair Drawing 8/4–32– 

0160, Issue 2, dated January 18, 2011; and 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011; for related 

information. 

Material Incorporated by Reference 

(l) You must use Bombardier Repair 

Drawing 8/4–32–0160, Issue 2, dated January 

18, 2011; or Bombardier Repair Drawing 8/ 

4–32–0160, Issue 3, dated February 15, 2011; 

as applicable; to do the actions required by 

this AD, unless the AD specifies otherwise. 

The issue dates for Bombardier Repair 

Drawing 8/4–32–0160, Issue 3, dated 

February 15, 2011, are identified on only the 

first page of that document. 

(1) The Director of the Federal Register 

approved the incorporation by reference of 

Bombardier Repair Drawing 8/4–32–0160, 

Issue 3, dated February 15, 2011, under 5 

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

(2) The Director of the Federal Register 

previously approved the incorporation by 

reference of Bombardier Repair Drawing 8/4– 

32–0160, Issue 2, dated January 18, 2011, on 

March 25, 2011 (76 FR 13080, March 10, 

2011). 

(3) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

e-mail thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. 

(4) 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. 

(5) 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 July 6, 

2011. 

Kalene C. Yanamura, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2011–17813 Filed 7–15–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF THE TREASURY 

Internal Revenue Service 

26 CFR Part 1 

[TD 9536] 

RIN 1545–BK40 

Determining the Amount of Taxes Paid 

for Purposes of the Foreign Tax Credit 

AGENCY: Internal Revenue Service (IRS), 

Treasury. 

ACTION: Final and temporary 

regulations. 

SUMMARY: This document contains final 

and temporary regulations providing 

guidance relating to the determination 

of the amount of taxes paid for purposes 

of the foreign tax credit. These 

regulations address certain highly 

structured arrangements that produce 

inappropriate foreign tax credit results. 

The regulations affect individuals and 

corporations that claim direct and 

indirect foreign tax credits. The text of 

these temporary regulations also serves 

as the text of the proposed regulations 

(REG–126519–11) published in the 

Proposed Rules section in this issue of 

the Federal Register. 

DATES: Effective Date: These regulations 

are effective on July 18, 2011. 

Applicability Date: For dates of 

applicability, see § 1.901–2T(h)(3). 

FOR FURTHER INFORMATION CONTACT: 

Jeffrey P. Cowan, at (202) 622–3850. 

SUPPLEMENTARY INFORMATION: 

Background 

On March 30, 2007, the Federal 

Register published proposed regulations 

mstockstill on DSK4VPTVN1PROD with RULES