## 17075 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / Rules and Regulations

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 ACO, send it to ATTN: James Delisio, 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, 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.

(i) Related Information

Refer to MCAI Canadian Airworthiness Directive CF–2011–37, dated October 19, 2011, and the service bulletins specified in paragraphs (i)(1), (i)(2), and (i)(3) of this AD, for related information.

(1) Bombardier Service Bulletin 601–0609, dated August 31, 2011.

(2) Bombardier Service Bulletin 604–71– 005, dated July 18, 2011.

(3) Bombardier Service Bulletin 605–71– 002, dated July 18, 2011.
(j) 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) Bombardier Service Bulletin 601–0609, dated August 31, 2011.

(ii) Bombardier Service Bulletin 604–71– 005, dated July 18, 2011.

(iii) Bombardier Service Bulletin 605–71– 002, dated July 18, 2011.

(3) 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; email thd.crj@aero.bombardier.com; Internet http:// www.bombardier.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 February 28, 2013. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2013–05587 Filed 3–19–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–1031; Directorate Identifier 2012–NE–31–AD; Amendment 39–**  **17391; AD 2013–05–19]**

**RIN 2120–AA64**



### Airworthiness Directives; Rolls-Royce **Deutschland Ltd & Co KG Turbofan Engines** 

**AGENCY**

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for certain Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611–8 turbofan engines. This AD requires inspection and replacement, if necessary, of affected bolts. This AD was prompted by a quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.

**DATES** 

### : This AD becomes effective April 24, 2013.

**ADDRESSES** 

### : The Docket Operations office is located at Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12–140, Washington, DC
20590–0001.

**FOR FURTHER INFORMATION CONTACT**

### : Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; email: frederick.zink@faa.gov; telephone: 781–238–7779; fax: 781–
238–7199.

**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 November 13, 2012 (77 FR 67582). That NPRM proposed to correct an unsafe condition for the specified products. The Mandatory Continuing Airworthiness Information states:

The results of a recent quality review of low pressure turbine (LPT) stage 1 static air seal and high pressure turbine (HPT) stage 1 air seal support bolts identified that, before installation, those bolts may have not been inspected. As a consequence, bolts with reduced material properties may have been installed in some engines.

This condition, if not detected and corrected, could lead to failure of a bolt, potentially causing turbine disc fracture and release of high-energy debris, possibly resulting in damage to the aeroplane and/or injury to the occupants.



### Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM (77 FR 67582, November 13, 2012). However, we changed paragraph (e) of this AD by removing the reporting requirement because that requirement is not necessary to correct the unsafe condition.

Conclusion

We reviewed the available data and determined that air safety and the public interest require adopting the AD as proposed (77 FR 67582, November 13, 2012). Costs of Compliance

Based on the service information, we estimate that this AD affects about 20 engines of U.S. registry. We also estimate that it will take about 4 hours per product to comply with this AD. The average labor rate is $85 per hour. Required parts will cost about $1,848 per engine. Based on these figures, we estimate the cost of the AD on U.S. operators to be $43,760. 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


## 17076 Federal Register / Vol. 78, No. 54 / Wednesday, March 20, 2013 / 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);

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 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 this AD, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (phone: (800) 647–5527) is provided 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: 2013–05–19 Rolls-Royce Deutschland Ltd & Co KG: Amendment 39–17391; Docket No. FAA–2012–1031; Directorate Identifier 2012–NE–31–AD.
(a) Effective Date

This airworthiness directive (AD) becomes effective April 24, 2013.
(b) Affected ADs

None. (c) Applicability

This AD applies to Rolls-Royce Deutschland Ltd & Co KG (RRD) Tay 611–8 turbofan engines, serial numbers 16245, 16256, 16417, 16418, 16584, 16585, 16639, 16640, 16701, 16702, 16813, 16814, 16853, 16854, 16879, 16880, 16898, 16905, 16906, 16911, 16923, 16935, and 16936, with a date of the last shop visit before December 8,
2006.
(d) Reason

This AD was prompted by a recent quality review determination that bolts with reduced material properties may have been installed in some engines. We are issuing this AD to prevent uncontained turbine disc fracture and damage to the airplane.
(e) Actions and Compliance

Unless already done, for engines with a date of the last shop visit before December 8, 2006, do the following actions:

(1) If engine cycles accumulated since the last engine shop visit is 5,400 cycles or more on the effective date of this AD, inspect the bolts installed in the low-pressure turbine (LPT) stage 1 static seal and high-pressure turbine (HPT) stage 1 air seal support within 100 engine cycles-in-service after the effective date of this AD.

(2) If engine cycles accumulated since the last engine shop visit is fewer than 5,400 cycles on the effective date of this AD, inspect the bolts installed in the LPT stage 1 static seal and HPT stage 1 air seal support before accumulating 5,500 engine cycles since the last engine shop visit.

(3) If you find any broken bolt, brown bolt, or bolt with a rough oxidized surface, then replace all bolts of the inspected engine flange with new bolts before further flight.
(f) Installation Prohibition

After the effective date of this AD, do not install any HPT module and/or LPT module into any engine, or any engine onto an airplane, unless the bolts have been inspected and replaced if necessary, as specified in paragraph (e) of this AD.
(g) Alternative Methods of Compliance (AMOCs)

The Manager, Engine Certification Office, FAA, may approve AMOCs to this AD. Use the procedures found in 14 CFR 39.19 to make your request.
(h) Related Information

(1) For more information about this AD, contact Frederick Zink, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7779; fax: 781–238–7199; email: frederick.zink@faa.gov. (2) Refer to European Aviation Safety Agency AD 2012–0163, dated August 28, 2012, and RRD Alert Service Bulletin TAY– 72–A1696, Revision 1, dated June 11, 2012, for related information.

(3) For service information identified in this AD, contact Rolls-Royce Deutschland Ltd & Co KG, Eschenweg 11, Dahlewitz, 15827 Blankenfelde-Mahlow, Germany; phone: 49 0 33–7086–1200 (direct 1016); fax: 49 0 33– 7086–1212. You may view this service information at the FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA. For information on the availability of this material at the FAA, call
781–238–7125. (i) Material Incorporated by Reference

None.

Issued in Burlington, Massachusetts, on March 7, 2013. Colleen M. D’Alessandro, Assistant Manager, Engine & Propeller Directorate, Aircraft Certification Service.
[FR Doc. 2013–06170 Filed 3–19–13; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2012–0795; Directorate Identifier 2008–SW–53–AD; Amendment 39–**  **17395; AD 2013–05–23]**

**RIN 2120–AA64**



### Airworthiness Directives; Eurocopter **France Helicopters**

**AGENCY**

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

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for Eurocopter France (Eurocopter) Model AS332C, L, and L1 helicopters to require a one-time inspection of the main rotor head (MRH) swash-plateupper bearing (bearing) for a nonsmooth point (friction point). This AD was prompted by a report of the premature deterioration of the MRH bearing of the rotating star installed on a Model AS332L1 helicopter. The actions of this AD are intended to detect deterioration of the MRH bearing and to prevent overloading the scissor links which drive the main rotor system, failure of the scissors links, and subsequent loss of control of the helicopter.

**DATES** 

### : This AD is effective April 24,
2013.

**ADDRESSES** 

### : For service information identified in this AD, contact American Eurocopter Corporation, 2701 Forum