52222 Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations 

4090; e-mail: jim.rutherford@faa.gov. Before 

using any approved AMOC on any airplane 

to which the AMOC applies, notify your 

appropriate principal inspector (PI) in the 

FAA Flight Standards District Office (FSDO), 

or lacking a PI, your local FSDO. 

(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: For any 

reporting requirement in this AD, 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 

(h) Refer to AGEˆNCIA NACIONAL DE 

AVIAC ̧A ̃ O CIVIL—BRAZIL (ANAC), NPR/AD 

2011–500–02, dated March 31, 2011; MCAI 

AGEˆNCIA NACIONAL DE AVIAC ̧A ̃ O 

CIVIL—BRAZIL (ANAC), AD No.: 2010–11– 

01, dated December 20, 2010; and PHENOM 

Service Bulletin SB No.: 500–27–0006, 

Revision No.: 02, dated January 14, 2011; for 

related information. 

Material Incorporated by Reference 

(i) You must use PHENOM Service Bulletin 

SB No.: 500–27–0006, Revision No.: 02, 

dated January 14, 2011, 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 EMBRAER Empresa 

Brasileira de Aerona ́utica S.A., Phenom 

Maintenance Support, Av. Brig. Farina Lima, 

2170, Sao Jose dos Campos–SP, CEP: 12227– 

901—P.O. Box: 36/2, BRASIL; telephone: 

++55 12 3927–5383; fax: ++55 12 3927–2619; 

e-mail: phenom.reliability@embraer.com.br; 

Internet: http://www.embraer.com.br. 

(3) You may review copies of the 

referenced service information at the FAA, 

Small Airplane Directorate, 901 Locust, 

Kansas City, Missouri 64106. For information 

on the availability of this material at the 

FAA, call (816) 329–4148. 

(4) You may also review copies of the 

service information incorporated by reference 

for this AD 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 Kansas City, Missouri on August 

9, 2011. 

Earl Lawrence, 

Manager, Small Airplane Directorate, Aircraft 

Certification Service. 

[FR Doc. 2011–20775 Filed 8–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0515; Directorate 

Identifier 2009–NM–196–AD; Amendment 

39–16776; AD 2011–17–12] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model CL–600–2C10 (Regional Jet 

Series 700, 701 & 702), Model CL–600– 

2D15 (Regional Jet Series 705), and 

Model CL–600–2D24 (Regional Jet 

Series 900) Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. 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: 

Several cases have been reported of cracks 

in the joint extrusions securing the outer 

bondment to the acoustic panel of the nacelle 

transcowl assemblies. Although there is no 

effect on flight safety (thrust reverser 

stowed), thrust reverser deployment under 

rejected take-off or emergency landing load 

conditions could potentially result in 

acoustic panel failure and possible runway 

debris. 

* * * * * 

The loss of an acoustic panel during 

rejected take-off or emergency landing 

load conditions could leave debris on 

the runway. This debris, if not removed, 

creates an unsafe condition for other 

airplanes during take-off or landing, as 

those airplanes could impact debris on 

the runway and sustain damage. We are 

issuing this AD to require actions to 

correct the unsafe condition on these 

products. 

DATES: This AD becomes effective 

September 26, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of September 26, 2011. 

ADDRESSES: You may examine the AD 

docket on the Internet at http:// 

www.regulations.gov or in person at the 

U.S. Department of Transportation, 

Docket Operations, M–30, West 

Building Ground Floor, Room W12–140, 

1200 New Jersey Avenue SE., 

Washington, DC. 

FOR FURTHER INFORMATION CONTACT: 

Craig Yates, 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– 

7355; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a supplemental notice of 

proposed rulemaking (NPRM) to amend 

14 CFR part 39 to include an AD that 

would apply to the specified products. 

That supplemental NPRM was 

published in the Federal Register on 

April 6, 2011 (76 FR 18957). That 

supplemental NPRM proposed to 

correct an unsafe condition for the 

specified products. The MCAI states: 

Several cases have been reported of cracks 

in the joint extrusions securing the outer 

bondment to the acoustic panel of the nacelle 

transcowl assemblies. Although there is no 

effect on flight safety (thrust reverser 

stowed), thrust reverser deployment under 

rejected take-off or emergency landing load 

conditions could potentially result in 

acoustic panel failure and possible runway 

debris. 

This [Canadian] directive mandates 

inspection, repair (if necessary) and 

reinforcement of the transcowl assemblies. 

The loss of an acoustic panel during 

rejected take-off or emergency landing 

load conditions could leave debris on 

the runway. This debris, if not removed, 

creates an unsafe condition for other 

airplanes during take-off or landing, as 

those airplanes could impact debris on 

the runway and sustain damage. The 

inspection is a detailed visual 

inspection of the outboard edge of the 

transcowl joint extrusion for evidence of 

cracking. The repair consists of doing an 

eddy current or liquid penetrant 

inspection for cracking, and depending 

on the results, either removing the 

affected joint extrusion area and 

replacing with packers, or contacting 

Bombardier for repair instructions and 

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Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations 52223 

doing the repair. The reinforcement of 

the transcowl assemblies includes 

installing new support channels. You 

may obtain further information by 

examining the MCAI in the AD docket. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. We 

considered the comments received. 

Request To Allow for Records Review 

American Eagle Airlines (AEA) 

requested that we revise the 

supplemental NPRM to allow operators 

to perform a records review in lieu of 

the inspection for part number, serial 

number, and repair status of each 

transcowl assembly, as required by 

paragraph (g) of the supplemental 

NPRM. AEA did not provide reasoning 

for this request. 

We agree to allow operators to 

perform a records review in lieu of the 

inspection for part number, serial 

number, and repair status of each 

transcowl assembly. We have 

determined that a review of airplane 

maintenance records is acceptable in 

lieu of the inspection, if the part 

number, serial number, and repair status 

of each transcowl assembly can be 

conclusively determined from that 

review. We have revised paragraph (g) 

of the final rule accordingly. 

Request To Revise Paragraph (g)(1) of 

the Supplemental NPRM 

AEA requested that we revise 

paragraph (g)(1) of the supplemental 

NPRM to remove the reference to 

paragraph (h) of the supplemental 

NPRM. AEA explained that the 

transcowls specified in paragraph (g)(1) 

of the supplemental NPRM are postmodified transcowls and do not need 

the inspections required by paragraph 

(h) of the supplemental NPRM. AEA 

reasoned that paragraph (h) of the 

supplemental NPRM should not apply 

to airplanes that have met the 

conditions specified in paragraph 

(g)(1)(i), (g)(1)(ii), or (g)(1)(iii) of the 

supplemental NPRM. 

We agree to revise paragraph (g)(1) of 

the final rule to remove reference to 

paragraph (h) of the final rule. We have 

determined that only paragraph (k) of 

the final rule applies to postmodification transcowls. We have 

revised paragraph (g)(1) of the final rule 

accordingly. 

Conclusion 

We reviewed the available data, 

including the comment received, and 

determined that air safety and the 

public interest require adopting the AD 

with the changes described previously. 

We determined that these changes will 

not increase the economic burden on 

any operator or increase the scope of the 

AD. 

Differences Between This 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 our FAA 

policies. Any such differences are 

highlighted in a Note within the AD. 

Costs of Compliance 

We estimate that this AD will affect 

361 products of U.S. registry. We also 

estimate that it will take about 8 workhours per product to comply with the 

basic requirements of this AD. The 

average labor rate is $85 per work-hour. 

Required parts will cost about $0 per 

product. Where the service information 

lists required parts costs that are 

covered under warranty, we have 

assumed that there will be no charge for 

these parts. As we do not control 

warranty coverage for affected parties, 

some parties may incur costs higher 

than estimated here. Based on these 

figures, we estimate the cost of this AD 

to the U.S. operators to be $245,480, or 

$680 per product. 

In addition, we estimate that any 

necessary follow-on actions would take 

between 4 and 8 work-hours and require 

parts costing $0, for a cost between $340 

and $680 per product. We have no way 

of determining the number of products 

that may need these actions. 

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. 

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 the NPRM, 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. 

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: 

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52224 Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations 

2011–17–12 Bombardier, Inc.: Amendment 

39–16776. Docket No. FAA–2010–0515; 

Directorate Identifier 2009–NM–196–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective September 26, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to the airplanes 

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

this AD, certificated in any category. 

(1) Bombardier, Inc. Model CL–600–2C10 

(Regional Jet Series 700, 701, & 702) 

airplanes, serial numbers 10003 through 

10265 inclusive. 

(2) Bombardier, Inc. Model CL–600–2D15 

(Regional Jet Series 705) and Model CL–600– 

2D24 (Regional Jet Series 900) airplanes, 

serial numbers 15001 through 15192 

inclusive. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 78: Engine exhaust. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

Several cases have been reported of cracks 

in the joint extrusions securing the outer 

bondment to the acoustic panel of the nacelle 

transcowl assemblies. Although there is no 

effect on flight safety (thrust reverser 

stowed), thrust reverser deployment under 

rejected take-off or emergency landing load 

conditions could potentially result in 

acoustic panel failure and possible runway 

debris. 

* * * * * 

The loss of an acoustic panel during rejected 

take-off or emergency landing load 

conditions could leave debris on the runway. 

This debris, if not removed, creates an unsafe 

condition for other airplanes during take-off 

or landing, as those airplanes could impact 

debris on the runway and sustain damage. 

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, Repair, and Reinforcement 

(g) Within 5,000 flight hours or 24 months 

after the effective date of this AD, whichever 

occurs first, inspect for the part number and 

serial number of each transcowl assembly, 

and, as applicable, the repair status of each 

transcowl assembly. A review of airplane 

maintenance records is acceptable in lieu of 

this inspection if the part number and serial 

number of each transcowl assembly, and, as 

applicable, the repair status of each 

transcowl assembly can be conclusively 

determined from that review. 

(1) If all transcowl assemblies installed on 

any airplane meet one of the conditions 

listed in paragraph (g)(1)(i), (g)(1)(ii), or 

(g)(1)(iii) of this AD, no further action is 

required by this AD, except paragraph (k) of 

this AD must be complied with. 

(i) Having part number (P/N) KCN624– 

2003–3, –4, –5, –6, –7, or –8, as listed in 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010. 

(ii) Having P/Ns CN624–2001–XXX or 

KCN624–2001–X (XXX and X mean various 

dash numbers), with serial number (S/N) 

SB0965 or higher. 

(iii) Having P/Ns CN624–2001–XXX or 

KCN624–2001–X (XXX and X mean various 

dash numbers), and repaired in accordance 

with one of the Bombardier repair 

engineering orders (REOs) listed in paragraph 

1.D. of Bombardier Service Bulletin 670BA– 

78–008, Revision B, dated December 22, 

2010; or paragraph 1.A. of Bombardier 

Service Bulletin 670SH–78–029, Revision C, 

dated November 10, 2010. 

(2) If one or more of the transcowl 

assemblies have P/N CN624–2001–XXX or 

KCN624–2001–X (XXX and X mean various 

dash numbers), with S/N SB0964 or lower, 

and have not been repaired in accordance 

with one of the Bombardier REOs listed in 

paragraph 1.D. of Bombardier Service 

Bulletin 670BA–78–008, Revision B, dated 

December 22, 2010; or paragraph 1.A. of 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010; do the 

actions specified in paragraph (i) of this AD. 

(h) As of the effective date of this AD, if 

any high-energy stop occurs and the thrust 

reversers are deployed above 68% N1, or if 

a rejected take-off (RTO) occurs and the 

thrust reversers are deployed above 68% N1: 

Perform a detailed inspection for cracks of 

each transcowl assembly (left, right, upper, 

and lower) before further flight, by doing the 

actions specified in paragraphs (h)(1), (h)(2), 

and (h)(3) of this AD. Doing the requirements 

of paragraph (i) of this AD terminates the 

requirements of paragraph (h) of this AD. 

(1) Open the cowling on the left and right 

engines. 

(2) Do a detailed inspection for cracks of 

the joint extrusion of the upper and lower 

transcowl assembly on the left and right 

engines at the location of the joint piece. If 

no cracks are found, close the cowlings on 

the left and right engines. 

(3) If any crack is found on one or more 

transcowl assemblies during the inspection 

required by paragraph (h)(2) of this AD, 

before further flight, repair and reinforce the 

cracked part(s) in accordance with paragraph 

(i)(1) of this AD. 

Note 1: Procedure—Part 3 of Task 05–51– 

27–210–801 of Chapter 05, Part 2, Volume 1, 

of the Bombardier CRJ Series Regional Jet 

Aircraft Maintenance Manual (AMM), CSP 

B–001, Revision 34, dated November 20, 

2010, provides guidance for opening and 

closing the cowling on the left and right 

engines. 

(i) For transcowl assemblies identified in 

paragraph (g)(2) of this AD: Except as 

required by paragraph (h) of this AD, within 

5,000 flight hours or 24 months after the 

effective date of this AD, whichever comes 

first, do a detailed inspection for cracking on 

each transcowl assembly, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 670BA–78–008, 

Revision B, dated December 22, 2010; or 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010. 

Accomplishment of the actions specified in 

paragraph (i)(1) or (i)(2) of this AD for all 

transcowl assemblies identified in paragraph 

(g)(2) of this AD terminates the requirements 

of paragraph (h) of this AD. 

(1) If any cracking of the joint extrusion is 

found, before further flight, repair and 

reinforce the joint extrusion on each 

transcowl assembly, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010; or Bombardier 

Service Bulletin 670SH–78–029, Revision C, 

dated November 10, 2010. 

(2) If no cracking is found, before further 

flight, reinforce the joint extrusion on each 

transcowl assembly, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010; or Bombardier 

Service Bulletin 670SH–78–029, Revision C, 

dated November 10, 2010. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(j) Inspections, repairs, and reinforcement 

of the joint extrusion on each transcowl is 

also acceptable for compliance with the 

corresponding requirements of paragraph (i) 

of this AD if done before the effective date 

of this AD in accordance with the service 

information listed in table 1 of this AD. 

TABLE 1—CREDIT SERVICE INFORMATION

Document Revision Date 

Bombardier Service Bulletin 670BA–78–008 ................................ Original ........................................................................ September 19, 2008. 

Bombardier Service Bulletin 670BA–78–008 ................................ A .................................................................................. July 10, 2009. 

Bombardier Service Bulletin 670SH–78–029 ................................ Original ........................................................................ July 3, 2008. 

Bombardier Service Bulletin 670SH–78–029 ................................ A .................................................................................. June 30, 2009. 

Bombardier Service Bulletin 670SH–78–029 ................................ B .................................................................................. November 25, 2009. 

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Federal Register / Vol. 76, No. 162 / Monday, August 22, 2011 / Rules and Regulations 52225 

Parts Installation 

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

replacement or spare transcowl assembly 

having P/N CN624–2001–XXX or KCN624– 

2001–X (XXX and X mean various dash 

numbers), with S/N SB0964 or lower, may be 

installed on any airplane, except for a 

transcowl assembly on which any repair 

listed in paragraph 1.D. of Bombardier 

Service Bulletin 670BA–78–008, Revision B, 

dated December 22, 2010, or paragraph 1.A. 

of Bombardier Service Bulletin 670SH–78– 

029, Revision C, dated November 10, 2010, 

has been done; and except for a transcowl 

that has been inspected as specified in 

paragraph (i) of this AD and all applicable 

actions specified in paragraph (i)(1) or (i)(2) 

of this AD, as applicable, have been done. 

FAA AD Differences 

Note 2: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

Other FAA AD Provisions 

(l) 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. If sending information directly 

to the NYACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

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 

(m) Refer to MCAI Canadian Airworthiness 

Directive CF–2009–33, dated July 28, 2009; 

Bombardier Service Bulletin 670BA–78–008, 

Revision B, dated December 22, 2010; and 

Bombardier Service Bulletin 670SH–78–029, 

Revision C, dated November 10, 2010; for 

related information. 

Material Incorporated by Reference 

(n) You must use Bombardier Service 

Bulletin 670BA–78–008, Revision B, dated 

December 22, 2010; and Bombardier Service 

Bulletin 670SH–78–029, Revision C, dated 

November 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 August 

8, 2011. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2011–20673 Filed 8–19–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2009–1213; Directorate 

Identifier 2009–NM–097–AD; Amendment 

39–16775; AD 2011–17–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model DC–9–81 (MD–81), 

DC–9–82 (MD–82), DC–9–83 (MD–83), 

DC–9–87 (MD–87), and MD–88 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for the 

products listed above. This AD requires 

repetitive inspections for cracking of the 

lower rear spar caps of the wings, and 

related investigative and corrective 

actions if necessary. This AD also 

requires repetitive inspections of certain 

repaired areas. This AD was prompted 

by reports of cracking of the wing rear 

spar lower cap at the outboard flap and 

inboard drive hinge at station 

Xrs=164.000; the cracking is due to 

material fatigue from normal flap 

operating loads. We are issuing this AD 

to detect and correct such fatigue 

cracking, which could result in fuel 

leaks, damage to the wing skin or other 

structure, and consequent reduced 

structural integrity of the wing. 

DATES: This AD is effective September 

26, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of September 26, 2011. 

ADDRESSES: For service information 

identified in this AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, 3855 

Lakewood Boulevard, MC D800–0019, 

Long Beach, California 90846–0001; 

telephone 206–544–5000, extension 2; 

fax 206–766–5683; e-mail 

dse.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You 

may review copies of the referenced 

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. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Management Facility 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 address for the 

Docket Office (phone: 800–647–5527) is 

Document Management Facility, U.S. 

Department of Transportation, Docket 

Operations, M–30, West Building 

Ground Floor, Room W12–140, 1200 

New Jersey Avenue, SE., Washington, 

DC 20590. 

FOR FURTHER INFORMATION CONTACT: 

Roger Durbin, Aerospace Engineer, 

Airframe Branch, ANM–120L, FAA, Los 

Angeles Aircraft Certification Office, 

3960 Paramount Boulevard, Lakewood, 

California 90712–4137; phone: (562) 

627–5233; fax: (562) 627–5210; e-mail: 

roger.durbin@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an airworthiness 

directive (AD) that would apply to the 

specified products. That NPRM 

published in the Federal Register on 

February 8, 2010 (75 FR 6162). That 

NPRM proposed to require repetitive 

inspections for cracking of the lower 

rear spar caps of the wings, and related 

investigative and corrective actions if 

necessary. That NPRM also proposed to 

require repetitive inspections of certain 

repaired areas. 

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