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###### Department of Transportation

###### Federal Aviation Administration

          - 14 CFR Part 39
          - [Docket No. FAA-2015-0625; Directorate Identifier 2015-NE-09-AD]
          - RIN 2120-AA64

# AGENCY:

Federal Aviation Administration (FAA), DOT.

# ACTION:

Notice of proposed rulemaking (NPRM).

# SUMMARY:

We propose to adopt a new airworthiness directive (AD) for certain serial number GE Aviation Czech s.r.o. M601E-11, M601E-11A, and M601F turboprop engines with certain part number (P/N) gas generator turbine (GGT) blades, installed. This proposed AD was prompted by the determination that certain GGT blades are susceptible to blade failure. This proposed AD would require removing from service any affected engine with certain GGT blades installed. We are proposing this AD to prevent GGT blade failure, which could lead to engine failure and loss of the airplane.

# DATES:

We must receive comments on this proposed AD by June 22, 2015.

# ADDRESSES:

You may send comments by any of the following methods:
      -  Federal eRulemaking Portal:                          Go to                          http://www.regulations.gov.                          Follow the instructions for submitting comments.                    
      -  Mail:                          Docket Management Facility, U.S. Department of Transportation, 1200 New Jersey Avenue SE., West Building Ground Floor, Room W12-140, Washington, DC 20590-0001.                    
      -  Hand Delivery:                          Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays.                    
      -  Fax:                          202-493-2251.                    

For service information identified in this proposed AD, contact GE Aviation Czech s.r.o., Beranových 65, 199 02 Praha 9—Letňany, Czech Republic; phone: +420 222 538 111; fax: +420 222 538 222. 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.

### Examining the AD Docket

                    You may examine the AD docket on the Internet at                     *http://www.regulations.gov*                     by searching for and locating Docket No. FAA-2015-0625; 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 proposed AD, the mandatory continuing airworthiness information (MCAI), the regulatory evaluation, any comments received, and other information. The address for the Docket Office (phone: 800-647-5527) is in the                     **ADDRESSES**                     section. Comments will be available in the AD docket shortly after receipt.                

# FOR FURTHER INFORMATION CONTACT:

                        Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email:                         *robert.green@faa.gov.*

# SUPPLEMENTARY INFORMATION:

## Comments Invited

                    We invite you to send any written relevant data, views, or arguments about this proposed AD. Send your comments to an address listed under the                     **ADDRESSES**                     section. Include “Docket No. FAA-2015-0625; Directorate Identifier 2015-NE-09-AD” at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this proposed AD. We will consider all comments received by the closing date and may amend this proposed AD based on those comments.                

                    We will post all comments we receive, without change, to                     *http://www.regulations.gov,*                     including any personal information you provide. We will also post a report summarizing each substantive verbal contact with FAA personnel concerning this proposed AD.                

## Discussion

The European Aviation Safety Agency (EASA), which is the Technical Agent for the Member States of the European Community, has issued EASA AD 2015-0015, dated January 30, 2015 (referred to hereinafter as “the MCAI”), to correct an unsafe condition for the specified products. The MCAI states:

It has been demonstrated that non-shot peened Gas Generator Turbine (GGT) blades are susceptible to blade separation in the shank area due to their reduced fatigue life.

This condition, if not corrected, could lead to an in-flight engine shutdown and, consequently, reduced control of the aeroplane.

                    You may obtain further information by examining the MCAI in the AD docket on the Internet at                     *http://www.regulations.gov*                     by searching for and locating Docket No. FAA-2015-0625.                

## Related Service Information under 1 CFR Part 51

                    GE Aviation Czech s.r.o. has issued Alert Service Bulletin (ASB) No. M601E-11/30, dated December 23, 2014, and ASB No. M601E-11/31, M601E-11A/18, M601F/28, dated December 23, 2014. The ASBs describe procedures for removal and replacement of GGT blades that are not shot peened. This service information is reasonably available; see                     **ADDRESSES**                     for ways to access this service information.                

## FAA's Determination and Requirements of This Proposed AD

This product has been approved by the aviation authority of the Czech Republic, and is approved for operation in the United States. Pursuant to our bilateral agreement with the European Community, EASA has notified us of the unsafe condition described in the MCAI and service information referenced above. We are proposing this AD because we evaluated all information provided by EASA and determined the unsafe condition exists and is likely to exist or develop on other products of the same type design. This proposed AD would require removing from service any affected engine with GGT blades installed that are not shot peened.

## Costs of Compliance

                    We estimate that this proposed AD affects one engine installed on an airplane of U.S. registry. We also estimate that it would take about 64 hours per engine to comply with this proposed AD. The average labor rate is $85 per hour. Required parts cost about                           ( print page 22137)                        $28,765 per engine. Based on these figures, we estimate the cost of this proposed AD on U.S. operators to be $34,205.                

## 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 proposed AD would not have federalism implications under Executive Order 13132. This proposed AD would 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 proposed regulation:

(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.

# List of Subjects in 14 CFR Part 39

      - Air transportation
      - Aircraft
      - Aviation safety
      - Incorporation by reference
      - Safety

## The Proposed Amendment

Accordingly, under the authority delegated to me by the Administrator, the FAA proposes to amend 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 

2. The FAA amends § 39.13 by adding the following new airworthiness directive (AD): 

**GE Aviation Czech s.r.o. (Type Certificate previously held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.):**                         Docket No. FAA-2015-0625; Directorate Identifier 2015-NE-09-AD.                    

## (a) Comments Due Date

We must receive comments by June 22, 2015.

## (b) Affected ADs

None.

## (c) Applicability

This AD applies to certain serial number (S/N) GE Aviation Czech s.r.o. M601E-11, M601E-11A, and M601F turboprop engine models, with gas generator turbine (GGT) blade, part number (P/N) M601-3372.6 or M601-3372.51, installed, as follows:

(1) Model M601E-11: S/Ns 862001, 863008, 894018, 034005, 034006, 034007, 034008, 041003, and 042002.

(2) Model M601E-11A: S/Ns 042003, 042004, 044001, 044002, and 961001.

(3) Model M601F: S/Ns 024001, 002001, 003001, 024001, 934001, 934002, 961001.

## (d) Reason

This AD was prompted by the determination that certain GGT blades are susceptible to blade failure. These blades are identified as blade P/Ns M601-3372.6 and M601-3372.51, and are installed on an engine S/N identified in paragraph (c) of this AD. We are issuing this AD to prevent GGT blade failure, which could lead to engine failure and loss of the airplane.

## (e) Actions and Compliance

Comply with this AD within the compliance times specified, unless already done. After the effective date of this AD:

(1) Do not return to service any affected engine with GGT blade, P/N M601-3372.6 or M601-3372.51, installed, after 300 hours time in service or six months, whichever occurs first, after the effective date of this AD.

(2) If the affected engines are subsequently disassembled or overhauled, the non-shot peened GGT blades, P/N M601-3372.6 or M601-3372.51, are not eligible for installation in any other engine after removal.

## (f) Alternative Methods of Compliance (AMOCs)

                        The Manager, Engine Certification Office, FAA, may approve AMOCs for this AD. Use the procedures found in 14 CFR 39.19 to make your request. You may email your request to:                         *ANE-AD-AMOC@faa.gov.*

## (g) Related Information

                        (1) For more information about this AD, contact Robert Green, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781-238-7754; fax: 781-238-7199; email:                         *robert.green@faa.gov.*

                        (2) Refer to MCAI European Aviation Safety Agency AD 2015-0015, dated January 30, 2015, for more information. You may examine the MCAI in the AD docket on the Internet at                         *http://www.regulations.gov*                         by searching for and locating it in Docket No. FAA-2015-0625.                    

(3) GE Aviation Czech s.r.o. Alert Service Bulletin (ASB) No. M601E-11/30, dated December 23, 2014, which is co-published as one document with M601D-1/31, M601Z/29, and M601T/24, and ASB No. M601E-11/31, M601E-11A/18, M601F/28, dated December 23, 2014, which is co-published as one document with M601D-1/32, M601Z/30, M601E/61, M601T/25, M601FS/12, M601F-22/25, M601F-32/23, and M601E-21/28, are not incorporated by reference in this AD. The ASBs can be obtained from GE Aviation Czech s.r.o. using the contact information in paragraph (g)(4) of this proposed AD.

(4) For service information identified in this proposed AD, contact GE Aviation Czech s.r.o., Beranových 65, 199 02 Praha 9—Letňany, Czech Republic; phone: +420 222 538 111; fax: +420 222 538 222.

(5) 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.

Issued in Burlington, Massachusetts, on April 7, 2015.

Ann C. Mollica,

Acting Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service.

[FR Doc. 2015-09002 Filed 4-20-15; 8:45 am]

 BILLING CODE 4910-13-P