## 1731 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations

for the power cable assembly replacement kit. Based on these figures, the cost of the AD on U.S. operators will be $13,504 per helicopter, or $418,624 for the fleet. 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

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 that this AD:

(1) Is not a ‘‘significant regulatory action’’ under Executive Order 12866;

(2) Is not a ‘‘significant rule’’ under DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979);

(3) Will not affect intrastate aviation in Alaska to the extent that it justifies making a regulatory distinction; and

(4) 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 an economic 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 adding the following new airworthiness directive (AD):
2012–26–11 Bell Helicopter Textron Inc.: Amendment 39–17306; Docket No. FAA–2012–0601; Directorate Identifier 2008–SW–033–AD. (a) Applicability

This AD applies to Bell Helicopter Textron Inc. (BHTI) Model 205A, 205A–1, and 205B helicopters with starter/generator power cable assemblies (power cable assemblies), part number (P/N) 205–075–902–017 and P/ N 205–075–911–007 installed, certificated in any category.
(b) Unsafe Condition

This AD defines the unsafe condition as the power cable assembly connector (connector) deterioration, which can cause a short in the connector potentially leading to a fire in the starter/generator. A fire would result in smoke in the cockpit, reducing visibility, and risking loss of control of the helicopter.
(c) Effective Date

This AD becomes effective February 13,
2013. (d) Compliance

You are responsible for performing each action required by this AD within the specified compliance time unless accomplished previously.
(e) Required Actions

Within six months, replace the power cable assemblies using the parts contained in starter/generator kit P/N CT205–07–94–1, perform a continuity test, and connect wires to the starter generator as follows:

(1) For Model 205A and 205A–1 helicopters, follow the Accomplishment Instructions, paragraphs 2 through 16(c), of BHTI Alert Service Bulletin No. 205–07–94, Revision A, dated December 8, 2008.

(2) For the Model 205B helicopters, follow the Accomplishment Instructions, paragraphs 2 through 16(c), of BHTI Alert Service Bulletin No. 205B–08–50, dated December 8,
2008. (f) Alternative Methods of Compliance (AMOCs)

(1) The Manager, Safety Management Group, FAA, may approve AMOCs for this AD. Send your proposal to: Andy Shaw, Aviation Safety Engineer, Safety Management Group, Rotorcraft Directorate, FAA, 2601 Meacham Blvd., Fort Worth, TX 76137; telephone (817) 222–5110; email andy.shaw@faa.gov

.

(2) For operations conducted under a 14 CFR part 119 operating certificate or under 14 CFR part 91, subpart K, we suggest that you notify your principal inspector, or lacking a principal inspector, the manager of the local flight standards district office or certificate holding district office before operating any aircraft complying with this AD through an AMOC.
(g) Subject

Joint Aircraft Service Component (JASC) Code: 2497, electrical power system wiring.
(h) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise.

(i) Bell Helicopter Textron Inc. Alert Service Bulletin No. 205–07–94, Revision A, dated December 8, 2008.

(ii) Bell Helicopter Textron Inc. Alert Service Bulletin No. 205B–08–50, dated December 8, 2008.

(3) For Bell Helicopter Textron Inc. service information identified in this AD, contact Bell Helicopter Textron, Inc., P.O. Box 482, Fort Worth, TX 76101; telephone (817) 280– 3391; fax (817) 280–6466; or at http:// www.bellcustomer.com/files/

.

(4) You may view this service information at FAA, Office of the Regional Counsel, Southwest Region, 2601 Meacham Blvd., Room 663, Fort Worth, Texas 76137. For information on the availability of this material at the FAA, call (817) 222–5110.

(5) You may view this 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/cfr/ index.html

.

Issued in Fort Worth, Texas, on December 20, 2012. Kim Smith, Directorate Manager, Rotorcraft Directorate, Aircraft Certification Service.
[FR Doc. 2012–31586 Filed 1–8–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1032; Directorate Identifier 2012–NM–079–AD; Amendment**  **39–17296; AD 2012–26–01]**

**RIN 2120–AA64**



### Airworthiness Directives; Saab AB, **Saab Aerosystems Airplanes**

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.


## 1732 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for all Saab AB, Saab Aerosystems Model SAAB 2000 airplanes. This AD was prompted by reports of chafing on the bottom panel of the center cabin. This AD requires a general visual inspection to determine if certain fasteners are installed, and related investigative and corrective actions. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect the structural integrity of the affected wing-to-fuselage connection.

**DATES** 

### : This AD becomes effective February 13, 2013.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of February 13, 2013.

**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, WA 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 October 2, 2012 (77 FR 60073). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information (MCAI)
states:

On two SAAB 2000 aeroplanes, signs of chafing have been found on the bottom panel of the centre cabin between fuselage station (STA) 562 and STA 622. The investigation results have shown that the chafing is caused by certain Hi Lok fasteners, installed as a repair during production, through the upper wing skin panel.

This condition, if not detected and corrected, could affect the structural integrity of the affected wing-to-fuselage connection.

To address this potential unsafe condition, SAAB issued Service Bulletin (SB) 2000–53– 057 to provide instructions for a general visual inspection to detect chafing in the area between the upper wing skin and the cabin centre bottom panel and to verify if there are Hi Lok fasteners installed with the collar up.

For the reasons described above, this [European Aviation Safety Agency (EASA)] AD requires a one-time inspection of the designated area, the accomplishment of corrective action(s) [repair], depending on findings, and the reporting of all inspection results * * *.

This [EASA] AD is considered an interim action and further AD action may follow.



### Related investigative actions include measuring the distance between the fastener and bottom panel and a boroscope inspection for chafing and damage of the bottom panel. 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 (77 FR 60073, October 2, 2012) 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. Costs of Compliance

We estimate that this AD will affect 10 products of U.S. registry. We alsoestimate that it will take about 4 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 $3,400, or $340 per product.

We have received no definitive data that would enable us to provide a cost estimate for the on-condition actions specified in 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 that 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);

3. Will not affect intrastate aviation in Alaska; and

4. 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 (77 FR 60073, October 2, 2012), 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:
2012–26–01 Saab AB, Saab Aerosystems: Amendment 39–17296. Docket No. FAA–2012–1032; Directorate Identifier 2012–NM–079–AD.


## 1733 Federal Register / Vol. 78, No. 6 / Wednesday, January 9, 2013 / Rules and Regulations

(a) Effective Date

This airworthiness directive (AD) becomes effective February 13, 2013.

(b) Affected ADs

None.
(c) Applicability

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

Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

This AD was prompted by reports of chafing on the bottom panel of the center cabin. We are issuing this AD to detect and correct any chafing on the bottom panel of the center cabin, which could affect thestructural integrity of the affected wing-tofuselage connection.
(f) Compliance

You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
(g) Inspection

Within 12 months after the effective date of this AD, do a general visual inspection of the area between the upper part of the wing skin and the center bottom panel to determine if any Hi Lok fasteners are installed with the collar up, and do all applicable related investigative actions, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000– 53–057, dated November 22, 2011.
(h) Repair

If any chafing or damage is found during any inspection required by paragraph (g) of this AD: Before further flight, repair in accordance with a method approved by the Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
(i) Reporting

Submit a report of the findings (both positive and negative) of the inspection required by paragraph (g) of this AD to Saab AB, Saab Aerosystems, in accordance with the Accomplishment Instructions of Saab Service Bulletin 2000–53–057, dated November 22, 2011, at the applicable time specified in paragraph (i)(1) or (i)(2) of this AD. The report must include the inspection results, the airplane serial number, and the number of landings and flight hours on the airplane.

(1) If the inspection was done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(2) If the inspection was done before the effective date of this AD: Submit the report within 30 days after the effective date of this
AD. (j) Other FAA AD Provisions 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: Shahram Daneshmandi, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057–3356; telephone 425–227–1112; fax 425–227–1149. Information may be emailed 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.
(k) Related Information

Refer to MCAI EASA Airworthiness Directive 2012–0068, dated April 25, 2012; and Saab Service Bulletin 2000–53–057, dated November 22, 2011; for related information.
(l) Material Incorporated by Reference

(1) The Director of the Federal Register approved the incorporation by reference (IBR) of the service information listed in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) You must use this service information as applicable to do the actions required by this AD, unless the AD specifies otherwise. (i) Saab Service Bulletin 2000–53–057, dated November 22, 2011.

(ii) Reserved. (3) For service information identified in this AD, contact Saab AB, Saab Aeronautics, SE–581 88, Linko  ̈ ping, Sweden; telephone +46 13 18 5591; fax +46 13 18 4874; email saab2000.techsupport@saabgroup.com; Internet http://www.saabgroup.com

.

(4) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For information on the availability of this material at the FAA, call 425–227–1221.

(5) You may view this 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/cfr/ibrlocations.html

.

Issued in Renton, Washington, on December 14, 2012. Kalene C. Yanamura, Acting Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2012–31035 Filed 1–8–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0820; Directorate Identifier 2010–NE–31–AD; Amendment 39–**  **17308; AD 2012–26–13]**

**RIN 2120–AA64**



### Airworthiness Directives; Thielert **Aircraft Engines GmbH Reciprocating Engines** 

**AGENCY** 

### : Federal Aviation Administration (FAA), DOT.

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are superseding an existing airworthiness directive (AD) for all Thielert Aircraft Engines GmbH models TAE 125–01, TAE 125–02–99, and TAE 125–02–114 reciprocating engines. That AD currently requires installation of full-authority digital electronic control (FADEC) software version 2.91. This new AD requires removing all software mapping versions prior to 292, 301, or 302, applicable to the TAE engine model. This AD was prompted by reports of possible power loss on airplanes equipped with TAE 125 engines. We are issuing this AD to prevent engine power loss or in-flight shutdown, resulting in reduced control of or damage to the airplane.

**DATES** 

### : This AD is effective February 13,
2013.

**ADDRESSES** 

### : For service information identified in this AD, contact Thielert