428 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

New Requirements of This AD 

Replacement 

(h) Within 120 months after the effective 

date of this AD, replace all midspar fuse pins 

having part number (P/N) 311A1092–2 with 

a midspar fuse pin having P/N 311A1092–3, 

in accordance with the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–54A1044, Revision 2, dated January 20, 

2010. Accomplishing the requirements of this 

paragraph terminates the requirements of 

paragraph (g) of this AD for that fuse pin. 

Actions Accomplished According to 

Previous Revision of Service Information 

(i) Actions done before the effective date of 

this AD in accordance with Boeing Special 

Attention Service Bulletin 737–54–1044, 

Revision 1, dated November 26, 2008, are 

acceptable for compliance with the 

corresponding requirements of this AD. 

Alternative Methods of Compliance 

(AMOCs) 

(j)(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. Send information to ATTN: Alan 

Pohl, Aerospace Engineer, Airframe Branch, 

ANM–120S, FAA, Seattle Aircraft 

Certification Office, 1601 Lind Avenue, SW., 

Renton, Washington 98057–3356; telephone 

(425) 917–6450; fax (425) 917–6590. 

Information may be e-mailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) To request a different method of 

compliance or a different compliance time 

for this AD, follow the procedures in 14 CFR 

39.19. Before using any approved AMOC on 

any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards District 

Office. The AMOC approval letter must 

specifically reference this AD. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved in accordance with 

the requirements of AD 2008–21–03 are 

acceptable for the corresponding 

requirements of this AD. 

Related Information 

(k) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue, SW., Renton, Washington 98057– 

3356; telephone (425) 917–6450; fax (425) 

917–6590; e-mail: alan.pohl@faa.gov. 

Material Incorporated by Reference 

(l) You must use Boeing Special Attention 

Service Bulletin 737–54–1044, dated 

December 10, 2007; or Boeing Alert Service 

Bulletin 737–54A1044, Revision 2, dated 

January 20, 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 

Boeing Alert Service Bulletin 737–54A1044, 

Revision 2, dated January 20, 2010, 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 Boeing Special Attention Service 

Bulletin 737–54–1044, dated December 10, 

2007, on November 13, 2008 (73 FR 59493, 

October 9, 2008). 

(3) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; e-mail me.boecom@boeing.com; 

Internet https://www.myboeingfleet.com. 

(4) You may review copies of the service 

information at the FAA, 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 an NARA facility, 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 

December 22, 2010. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2010–33003 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0959; Directorate 

Identifier 2010–NM–119–AD; Amendment 

39–16564; AD 2011–01–10] 

RIN 2120–AA64 

Airworthiness Directives; Bombardier, 

Inc. Model BD–700–1A10 and BD–700– 

1A11 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: 

There have been two in-service reports of 

main landing gear (MLG) tire failure on 

landing, during which a flailing tire tread 

caused damage to No. 2 and No. 3 hydraulic 

system lines in the wing auxiliary spar area 

on the left side of the aircraft. This damage 

resulted in the loss of supply pressure to the 

inboard and outboard brakes, as the only 

remaining braking source available was the 

No. 3 hydraulic system accumulator. The 

degradation of the brake system performance 

could adversely affect the aircraft during 

landing. 

* * * * * 

The unsafe condition is loss of braking 

capability, which could reduce the 

ability of the flightcrew to safely land 

the airplane. We are issuing this AD to 

require actions to correct the unsafe 

condition on these products. 

DATES: This AD becomes effective 

February 9, 2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of February 9, 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: 

Christopher Alfano, 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– 

7340; fax (516) 794–5531. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to include an AD that would 

apply to the specified products. That 

NPRM was published in the Federal 

Register on October 15, 2010 (75 FR 

63420). That NPRM proposed to correct 

an unsafe condition for the specified 

products. The MCAI states: 

There have been two in-service reports of 

main landing gear (MLG) tire failure on 

landing, during which a flailing tire tread 

caused damage to No. 2 and No. 3 hydraulic 

system lines in the wing auxiliary spar area 

on the left side of the aircraft. This damage 

resulted in the loss of supply pressure to the 

inboard and outboard brakes, as the only 

remaining braking source available was the 

No. 3 hydraulic system accumulator. The 

degradation of the brake system performance 

could adversely affect the aircraft during 

landing. 

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Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 429 

This directive mandates the relocation of 

the No. 2 and No. 3 hydraulic system lines 

in the wing auxiliary spar area on the left 

side of the aircraft, together with a 

modification to the left wing rib and debris 

shield, in order to prevent damage to the 

hydraulic lines in the event of a MLG tire 

failure. The debris shield on the right side is 

also modified for part commonality. 

The unsafe condition is loss of braking 

capability, which could reduce the 

ability of the flightcrew to safely land 

the airplane. 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 

received no comments on the NPRM or 

on the determination of the cost to the 

public. 

Conclusion 

We reviewed the available data and 

determined that air safety and the 

public interest require adopting the AD 

as proposed. 

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 

115 products of U.S. registry. We also 

estimate that it will take 40 work-hours 

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 $4,855 

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 

$949,325, or $8,255 per product. 

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: 

2011–01–10 Bombardier, Inc.: Amendment 

39–16564. Docket No. FAA–2010–0959; 

Directorate Identifier 2010–NM–119–AD. 

Effective Date 

(a) This airworthiness directive (AD) 

becomes effective February 9, 2011. 

Affected ADs 

(b) None. 

Applicability 

(c) This AD applies to Bombardier, Inc. 

Model BD–700–1A10 and BD–700–1A11 

airplanes, serial numbers 9002 through 9401 

inclusive, certificated in any category. 

Subject 

(d) Air Transport Association (ATA) of 

America Code 29: Hydraulic power. 

Reason 

(e) The mandatory continuing 

airworthiness information (MCAI) states: 

There have been two in-service reports of 

main landing gear (MLG) tire failure on 

landing, during which a flailing tire tread 

caused damage to No. 2 and No. 3 hydraulic 

system lines in the wing auxiliary spar area 

on the left side of the aircraft. This damage 

resulted in the loss of supply pressure to the 

inboard and outboard brakes, as the only 

remaining braking source available was the 

No. 3 hydraulic system accumulator. The 

degradation of the brake system performance 

could adversely affect the aircraft during 

landing. 

* * * * * 

The unsafe condition is loss of braking 

capability, which could reduce the ability of 

the flightcrew to safely land the airplane. 

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. 

Actions 

(g) Within 30 months after the effective 

date of this AD, relocate the No. 2 and No. 

3 hydraulic system lines in the wing 

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430 Federal Register / Vol. 76, No. 3 / Wednesday, January 5, 2011 / Rules and Regulations 

auxiliary spar area on the left side of the 

aircraft, and modify the left wing rib and left 

and right debris shields, in accordance with 

the Accomplishment Instructions of 

Bombardier Service Bulletin 700–29–021 (for 

Model BD–700–1A10 airplanes) or 700– 

1A11–29–004 (for Model BD–700–1A11 

airplanes), both Revision 01, both dated 

January 25, 2010, as applicable. 

Credit for Actions Accomplished in 

Accordance With Previous Service 

Information 

(h) Actions accomplished before the 

effective date of this AD in accordance with 

Bombardier Service Bulletin 700–29–021 or 

700–1A11–29–004, both dated April 3, 2009, 

as applicable, are considered acceptable for 

compliance with the corresponding actions 

specified in this AD. 

FAA AD Differences 

Note 1: This AD differs from the MCAI 

and/or service information as follows: No 

differences. 

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. 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 

on any airplane to which the AMOC applies, 

notify your principal maintenance inspector 

(PMI) or principal avionics inspector (PAI), 

as appropriate, or lacking a principal 

inspector, your local Flight Standards 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. 

(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 

(j) Refer to MCAI Canadian Airworthiness 

Directive CF–2010–10, dated March 26, 2010; 

and Bombardier Service Bulletins 700–29– 

021 and 700–1A11–29–004, both Revision 

01, both dated January 25, 2010; for related 

information. 

Material Incorporated by Reference 

(k) You must use Bombardier Service 

Bulletin 700–29–021, Revision 01, dated 

January 25, 2010; or Bombardier Service 

Bulletin 700–1A11–29–004, Revision 01, 

dated January 25, 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 

December 17, 2010. 

Ali Bahrami, 

Manager, Transport Airplane Directorate, 

Aircraft Certification Service. 

[FR Doc. 2010–32996 Filed 1–4–11; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2010–0953; Directorate 

Identifier 2010–NM–010–AD; Amendment 

39–16565; AD 2011–01–11] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Model MD–90–30 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 high frequency eddy current 

inspections for cracking on the hinge 

bearing lugs of the left and right sides 

of the center section ribs of the 

horizontal stabilizer, and related 

investigative and corrective actions if 

necessary. This AD was prompted by 

reports of cracks found on either the left 

or right (or in one case, both) sides of 

the center section ribs of the horizontal 

stabilizer. We are issuing this AD to 

detect and correct cracking in the hinge 

bearing lugs of the center section of the 

left and right ribs, which could result in 

failure of the hinge bearing lugs and 

consequent inability of the horizontal 

stabilizer to sustain the required loads. 

DATES: This AD is effective February 9, 

2011. 

The Director of the Federal Register 

approved the incorporation by reference 

of a certain publication listed in the AD 

as of February 9, 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 

(ACO), 3960 Paramount Boulevard, 

Lakewood, California 90712–4137; 

telephone (562) 627–5233; fax (562) 

627–5210. 

SUPPLEMENTARY INFORMATION: 

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