## 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.


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

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


## 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 Co ˆ teVertu 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** 

### :