## 13072 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

675704; e-mail RApublications@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm.

(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 February 22, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5115 Filed 3–9–11; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–1198; Directorate Identifier 2010–NM–145–AD; Amendment**  **39–16623; AD 2011–05–13]**

**RIN 2120–AA64**



### Airworthiness Directives; Saab AB, **Saab Aerosystems Model SAAB 2000 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:

Corrosion has been found on the rear spar upper cap of the horizontal stabilizer of SAAB 2000 aeroplanes. The affected areas are adjacent to the inboard elevator hinge where the electrical wiring harnesses are located and wired through the lightening holes. The upper spar cap is a primary structural element and is important to the structural integrity of the horizontal stabilizer.

Corrosion damage in these areas, if not detected and corrected, can result in a starting point for future crack propagation, which would impair the integrity of the horizontal stabilizer upper spar cap structure.


### * * * * * We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective April 14, 2011.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of April 14, 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** 

### : Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM– 116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1112; fax (425) 227–1149.

**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 December 14, 2010 (75 FR 77796). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Corrosion has been found on the rear spar upper cap of the horizontal stabilizer of SAAB 2000 aeroplanes. The affected areas are adjacent to the inboard elevator hinge where the electrical wiring harnesses are located and wired through the lightening holes. The upper spar cap is a primary structural element and is important to the structural integrity of the horizontal stabilizer.

Corrosion damage in these areas, if not detected and corrected, can result in a starting point for future crack propagation, which would impair the integrity of the horizontal stabilizer upper spar cap structure.

For the reasons describe above, this AD requires a detailed visual inspection (DVI) of the LH and RH horizontal stabilizer rear spar adjacent to the inboard elevator hinge and the harnesses installed in the adjacent areas, installation of convoluted tubing on the harness, and corrective actions depending on findings.



### The corrective actions include installing convoluted tubing on the harness, applying corrosion prevention compound to the inspected area, making sure clearance exists between the spar cap and the harnesses/convoluted tube, and contacting Saab for repair instructions and doing the repair. 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 8 products of U.S. registry. We alsoestimate that it will take about 2 workhours per product to comply with the basic requirements of this AD. The average labor rate is $85 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operators to be $1,360 or $170 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


## 13073 Federal Register / Vol. 76, No. 47 / Thursday, March 10, 2011 / Rules and Regulations

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: 2011–05–13 Saab AB, Saab Aerosystems: Amendment 39–16623. Docket No. FAA–2010–1198; Directorate Identifier 2010–NM–145–AD. Effective Date (a) This airworthiness directive (AD) becomes effective April 14, 2011.

Affected ADs

(b) None. Applicability

(c) This AD applies to all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes, certificated in any category. Subject

(d) Air Transport Association (ATA) of America Code 55: Stabilizers.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Corrosion has been found on the rear spar upper cap of the horizontal stabilizer of SAAB 2000 aeroplanes. The affected areas are adjacent to the inboard elevator hinge where the electrical wiring harnesses are located and wired through the lightening holes. The upper spar cap is a primary structural element and is important to the structural integrity of the horizontal stabilizer.

Corrosion damage in these areas, if not detected and corrected, can result in a starting point for future crack propagation, which would impair the integrity of the horizontal stabilizer upper spar cap structure.


### * * * * *
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 12 months after the effective date of this AD: Do a detailed visual inspection for corrosion of the left-hand and right-hand horizontal stabilizers, do a detailed visual inspection for chafing or damage on the harness installed in the adjacent area, and install convoluted tubing on the harness, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–55–013, dated July 6, 2009.

(h) If, during the inspection required by paragraph (g) of this AD, corrosion is found, before next flight, repair the corrosion using a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, or European Aviation Safety Agency (EASA) (or its delegated agent).

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, 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. Send information to Attn: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057– 3356; telephone (425) 227–1112; fax (425) 227–1149. 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

(j) Refer to MCAI EASA Airworthiness Directive 2010–0115, dated June 17, 2010; and Saab Service Bulletin 2000–55–013, dated July 6, 2009; for related information.
Material Incorporated by Reference

(k) You must use Saab Service Bulletin 2000–55–013, dated July 6, 2009, 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 Saab AB, Saab Aerosystems, SE–581 88, Linko  ̈ ping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; e-mail saab2000.techsupport@saabgroup.com;
Internet http://www.saabgroup.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 February 22, 2011. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2011–5116 Filed 3–9–11; 8:45 am]

**BILLING CODE 4910–13–P**