
[Federal Register Volume 80, Number 166 (Thursday, August 27, 2015)]
[Rules and Regulations]
[Pages 51935-51936]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-21119]



 ========================================================================
 Rules and Regulations
                                                 Federal Register
 ________________________________________________________________________
 
 This section of the FEDERAL REGISTER contains regulatory documents 
 having general applicability and legal effect, most of which are keyed 
 to and codified in the Code of Federal Regulations, which is published 
 under 50 titles pursuant to 44 U.S.C. 1510.
 
 The Code of Federal Regulations is sold by the Superintendent of Documents. 
 Prices of new books are listed in the first FEDERAL REGISTER issue of each 
 week.
 
 ========================================================================
 

  Federal Register / Vol. 80, No. 166 / Thursday, August 27, 2015 / 
Rules and Regulations  

[[Page 51935]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-0625; Directorate Identifier 2015-NE-09-AD; 
Amendment 39-18253; AD 2015-17-20]
RIN 2120-AA64


Airworthiness Directives; GE Aviation Czech s.r.o. Turboprop 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule.

-----------------------------------------------------------------------

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
serial number (S/N) 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 AD requires removing from service 
any affected engine with certain GGT blades installed. This AD was 
prompted by the determination that certain GGT blades are susceptible 
to blade failure. We are issuing this AD to prevent GGT blade failure, 
which could lead to engine failure and loss of the airplane.

DATES: This AD becomes effective October 1, 2015.

ADDRESSES: See the FOR FURTHER INFORMATION CONTACT section.

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 Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this 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 
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: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on April 21, 2015 (80 FR 
22136). The NPRM proposed 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.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We received no comments on the NPRM (80 FR 22136, April 21, 
2015).
    In our review of the NPRM, we found that we had included an S/N 
from the MCAI that was in error. We corrected the error by removing S/N 
961001 from paragraph (c)(2) of this AD.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting this AD with the changes described 
previously. We determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Costs of Compliance

    We estimate that this 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 AD. The average labor rate is $85 
per hour. Required parts cost about $28,765 per engine. Based on these 
figures, we estimate the cost of this 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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

[[Page 51936]]

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

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2015-17-20 GE Aviation Czech s.r.o. (Type Certificate previously 
held by WALTER Engines a.s., Walter a.s., and MOTORLET a.s.): 
Amendment 39-18253; Docket No. FAA-2015-0625; Directorate Identifier 
2015-NE-09-AD.

(a) Effective Date

    This AD becomes effective October 1, 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, and 044002.
    (3) Model M601F: S/Ns 024001, 002001, 003001, 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 http://www.regulations.gov/#!documentDetail;D=FAA-2015-0625-0002.

(h) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on August 20, 2015.
Colleen M. D'Alessandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-21119 Filed 8-26-15; 8:45 am]
 BILLING CODE 4910-13-P


