Airworthiness Directives; General Electric Company Turbofan Engines, 17945-17947 [2017-07477]

Download as PDF Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules (1) A minor transient would not significantly reduce safety margins and would involve flightcrew actions that are well within their capabilities. A minor transient may involve a slight increase in flightcrew workload or some physical discomfort to passengers or cabin crew. (2) A significant transient may lead to a significant reduction in safety margins, an increase in flightcrew workload, discomfort to the flightcrew, or physical distress to the passengers or cabin crew, possibly including non-fatal injuries. Significant transients do not require—in order to remain within or recover to the normal flight envelope— any of the following: (i) Exceptional piloting skill, alertness, or strength. (ii) Forces applied by the pilot which are greater than those specified in § 23.143(c). (iii) Accelerations or attitudes in the airplane that might result in further hazard to secured or non-secured occupants. 11.43 and 11.45, by any of the following methods: • Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments. • Fax: 202–493–2251. • Mail: U.S. Department of Transportation, Docket Operations, M– 30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue SE., Washington, DC 20590. • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. For service information identified in this NPRM, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552– 3329; email: geae.aoc@ge.com. You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238– 7125. Issued in Kansas City, Missouri on April 4, 2017. Pat Mullen, Acting Manager, Small Airplane Directorate, Aircraft Certification Service. Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). Examining the AD Docket You may examine the AD docket on the Internet at https:// www.regulations.gov by searching for and locating Docket No. FAA–2017– 0164; 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 proposed AD, the regulatory evaluation, any comments received, and other information. The street 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: Martin Adler, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238–7157; fax: 781–238–7199; email: martin.adler@faa.gov. SUPPLEMENTARY INFORMATION: We propose to adopt a new airworthiness directive (AD) for certain General Electric Company (GE) CF34–8 model turbofan engines. This proposed AD was prompted by analysis that resulted in the reduction of the life of the affected fan blades. This proposed AD would require inspections of the affected fan blades until their removal. We are proposing this AD to correct the unsafe condition on these products. DATES: We must receive comments on this proposed AD by May 30, 2017. ADDRESSES: You may send comments, using the procedures found in 14 CFR Comments Invited We invite you to send any written relevant data, views, or arguments about this NPRM. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2017–0164; Directorate Identifier 2017– NE–06–AD’’ at the beginning of your comments. We specifically invite comments on the overall regulatory, economic, environmental, and energy aspects of this NPRM. We will consider all comments received by the closing date and may amend this NPRM because of those comments. [FR Doc. 2017–07382 Filed 4–13–17; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2017–0164; Directorate Identifier 2017–NE–06–AD] RIN 2120–AA64 Airworthiness Directives; General Electric Company Turbofan Engines AGENCY: jstallworth on DSK7TPTVN1PROD with PROPOSALS SUMMARY: VerDate Sep<11>2014 13:41 Apr 13, 2017 Jkt 241001 PO 00000 Frm 00003 Fmt 4702 Sfmt 4702 17945 We will post all comments we receive, without change, to https:// www.regulations.gov, including any personal information you provide. We will also post a report summarizing each substantive verbal contact we receive about this NPRM. Discussion We learned that GE has determined, based on analysis, that the stresses in the pinholes in the affected fan blade could result in crack initiation at pinhole surfaces beyond 19,000, 19,500, or 25,000 cyles-since-new (CSN), depending on the engine model on which the blade is installed. GE, therefore, has initiated a program of initial and repetitive eddy current inspections (ECIs) and removal of this fan blade before it reaches 41,000 CSN. GE also provided an option to repair the blade which allows for an additional 28,000 cycles before it must be removed. This condition, if not corrected, could result in failure of the fan blade, uncontained blade release, damage to the engine, and damage to the airplane. Related Service Information Under 1 CFR Part 51 We reviewed GE Alert Service Bulletins (ASBs) CF34–8C SB 72–A0137 R05, dated June 15, 2016; and CF34–8E SB 72–A0060 R05, dated June 15, 2016. These ASBs provide the procedures necessary for calculating the adjusted CSN for the initial inspection. This service information is reasonably available because the interested parties have access to it through their normal course of business or by the means identified in the ADDRESSES section. Other Related Service Information We reviewed GE ASB CF34–8E SB 72–A0115 R03, issued on December 9, 2016, and GE ASB CF34–8C SB 72– A0225 R03, issued on December 9, 2016. The ASB’s describe procedures for repairing fan blade, part number (P/N) 4114T15P02, to P/N 4114T31G01 with the installation of a bushing in the pinholes. FAA’s Determination We are proposing this AD because we evaluated all the relevant information and determined the unsafe condition described previously is likely to exist or develop in other products of the same type design. Proposed AD Requirements This proposed AD would require initial and repetitive ECIs of the affected fan blade. This proposed AD would also require removal or repair of the affected fan blade at a reduced life. A fan blade E:\FR\FM\14APP1.SGM 14APP1 17946 Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules that has been repaired is eligible for an additional 28,000 cycles in service before it must be removed. Differences Between This Proposed AD and the Service Information The determination in this proposed AD of CSN, when CSN is not known, is simpler and clearer than the method indicated in the service information. The service information has several options that may lead to confusion among operators in making this determination. Costs of Compliance We estimate that this proposed AD affects 1,986 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this proposed AD: ESTIMATED COSTS Action Labor cost Initial ECI Inspection ....................................... Replacement of fan blade (prorated annual cost). 4 work-hours × $85 per hour = $340 ............. 0 work-hours × $85 per hour = $0 ................. 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. jstallworth on DSK7TPTVN1PROD with PROPOSALS 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 VerDate Sep<11>2014 13:41 Apr 13, 2017 Jkt 241001 Parts cost 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 Cost per product $0 5,460 $340 5,460 Cost on U.S. operators $675,240 10,843,560 (d) Subject Joint Aircraft System Component (JASC) Code 7230, Turbine Engine Compressor Section. (e) Unsafe Condition This AD was prompted by analysis that resulted in the reduction of the life of the affected fan blades. We are issuing this AD to prevent failure of the fan blade, uncontained blade release, damage to the engine, and damage to the airplane. (f) Compliance Comply with this AD within the compliance times specified, unless already done. (g) Eddy Current Inspections (ECIs) 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): ■ General Electric Company: Docket No. FAA– 2017–0164; Directorate Identifier 2017– NE–06–AD. (a) Comments Due Date We must receive comments by May 30, 2017. (b) Affected ADs None. (c) Applicability This AD applies to General Electric Company (GE) CF34–8C1, CF34–8C5, CF34– 8C5A1, CF34–8C5B1, CF34–8C5A2, CF34– 8C5A3, CF34–8E2, CF34–8E2A1, CF34–8E5, CF34–8E5A1, CF34–8E5A2, CF34–8E6 and CF34–8E6A1 engines, including engines marked on the engine data plate as CF34– 8C5B1/B, CF34–8C5/B, CF34–8C5A1/B, CF34–8C5A2/B, CF34–8C5/M, CF34–8C5A1/ M, CF34–8C5A2/M, CF34–8C5A3/B, or CF34–8C5B1/M, with a fan blade, part number (P/N) 4114T15P02 or P/N 4114T31G01, installed. PO 00000 Frm 00004 Fmt 4702 Sfmt 4702 (1) For CF34–8C1, CF34–8C5B1, CF34– 8C5B1/B and CF34–8E2 engines with fan blade, P/N 4114T15P02, installed: (i) Perform an initial ECI of the fan blade pinhole prior to the fan blade accumulating 25,000 cycles-since-new (CSN); and (ii) Repeat this inspection within every 3,000 cycles thereafter. (2) For CF34–8C5, CF34–8C5/B, CF34– 8C5A1, CF34–8C5A1/B, CF34–8C5A2, CF34– 8C5A2/B, CF34–8E2A1, CF34–8E5, CF34– 8E5A1, CF34–8E6 and CF34–8E6A1 engines with fan blade, P/N 4114T15P02, installed: (i) Perform an initial ECI of the fan blade pinhole prior to the fan blade accumulating 19,500 CSN; and (ii) Repeat this inspection within every 3,000 cycles thereafter, until the fan blade has accumulated 25,000 CSN, then repeat the inspection every 1,500 cycles thereafter. (3) For CF34–8C5/M, CF34–8C5A1/M, CF34–8C5A2/M, CF34–8C5A3, CF34–8C5A3/ B, CF34–8C5B1/M, and CF34–8E5A2 engines with fan blade, P/N 4114T15P02, installed: (i) Perform an initial ECI of the fan blade pinhole prior to the fan blade accumulating 19,000 CSN; and (ii) Repeat this inspection within every 3,000 cycles thereafter, until the fan blade has accumulated 25,000 CSN, then repeat the inspection every 1,500 cycles thereafter. (4) For any affected engine with a fan blade, P/N 4114T15P02, installed where the CSN of the fan blade is unknown on the effective date of this AD: E:\FR\FM\14APP1.SGM 14APP1 Federal Register / Vol. 82, No. 71 / Friday, April 14, 2017 / Proposed Rules (i) Assume the blade has accumulated 25,000 CSN on the effective date of this AD; and (ii) Inspect the blade prior to installation or within 500 cycles after the effective date of this AD, whichever is earlier. (5) If a fan blade is moved from one affected engine model to another affected model after the initial ECI: (i) Perform an additional ECI of the blade prior to installation in the new model; and (ii) Repeat this inspection based on the intervals of the new engine installation, as specified in paragraph (g) of this AD. (6) If a fan blade, P/N 4114T15P02, has been used on more than one engine model prior to the initial ECI, use Appendix A of GE Alert Service Bulletin (ASB) CF34–8C SB 72–A0137 R05, dated June 15, 2016, or Appendix A of GE ASB CF34–8E SB 72– A0060 R05, dated June 15, 2016, to calculate the new cycle limit for the initial inspection of that fan blade. Issued in Burlington, Massachusetts, on April 5, 2017. Carlos A. Pestana, Acting Manager, Engine & Propeller Directorate, Aircraft Certification Service. (h) Fan Blade Removal SUMMARY: (1) For any affected engine with a fan blade, P/N 4114T15P02, installed, remove the blade from service or repair to P/N 4114T31G01 prior to the blade accumulating 41,000 CSN. (2) For any affected engine with a fan blade, P/N 4114T31G01, installed, remove the blade from service prior to the blade accumulating 28,000 cycles since installation of the pinhole bushing. (i) 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. jstallworth on DSK7TPTVN1PROD with PROPOSALS (j) Related Information (1) For more information about this AD, contact Martin Adler, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; phone: 781–238– 7157; fax: 781–238–7199; email: martin.adler@faa.gov. (2) GE ASBs: CF34–8C SB 72–A0137 R05, dated June 15, 2016; CF34–8E SB 72–A0060 R05, dated June 15, 2016; CF34–8E SB 72A0115 R03, issued December 9, 2016; and CF34–8C ASB 72–A0225 R03, issued December 9, 2016; can be obtained from GE using the contact information in paragraph (j)(3) of this AD. (3) For service information identified in this proposed AD, contact General Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 45215, phone: 513–552–3272; fax: 513–552–3329; email: geae.aoc@ge.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, 1200 District Avenue, Burlington, MA. For information on the availability of this material at the FAA, call 781–238–7125. VerDate Sep<11>2014 13:41 Apr 13, 2017 Jkt 241001 [FR Doc. 2017–07477 Filed 4–13–17; 8:45 am] BILLING CODE 4910–13–P CONSUMER PRODUCT SAFETY COMMISSION 16 CFR Parts 1500 and 1507 [Docket No. CPSC–2006–0034] Amendments to Fireworks Regulations; Notice of Extension of Comment Period Consumer Product Safety Commission. ACTION: Extension of comment period. AGENCY: The Consumer Product Safety Commission (Commission or CPSC) published a notice of proposed rulemaking (NPR) regarding fireworks in the Federal Register on February 2, 2017. The NPR invited the public to submit written comments during a 75day comment period beginning on the NPR publication date. In response to a request for an extension of the comment period, the Commission is extending the comment period by 90 days. DATES: Submit comments by July 17, 2017. You may submit comments, identified by Docket No. CPSC–2006– 0034, electronically or in writing: Electronic Submissions: You may submit electronic comments to the Federal eRulemaking Portal at: https:// www.regulations.gov, by following the instructions for submitting comments. The Commission does not accept comments submitted by electronic mail (email), except through www.regulations.gov. Written Submissions: You may submit written comments by mail, hand delivery, or courier to: Office of the Secretary, Consumer Product Safety Commission, Room 820, 4330 East West Highway, Bethesda, MD 20814; telephone (301) 504–7923. Instructions: All submissions must include the agency name and docket number for this notice. All comments may be posted to https:// www.regulations.gov without change, including any personal identifiers, contact information, or other personal information. Do not submit confidential business information, trade secret information, or other sensitive or protected information that you do not want to be available to the public. If you ADDRESSES: PO 00000 Frm 00005 Fmt 4702 Sfmt 4702 17947 submit such information, the Commission recommends that you do so by mail, hand delivery, or courier. Docket: To read background documents or comments regarding this rulemaking, go to: https:// www.regulations.gov, insert docket number CPSC–2006–0034 in the ‘‘Search’’ box, and follow the prompts. SUPPLEMENTARY INFORMATION: On February 2, 2017, the Commission published an NPR in the Federal Register, proposing amendments to the fireworks regulations in 16 CFR parts 1500 and 1507, under the authority of the Federal Hazardous Substances Act (15 U.S.C. 1261–1278). 82 FR 9012. The NPR provided a 75-day comment period, which will close on April 18, 2017. The National Fireworks Association has requested that the Commission extend the comment period an additional 90 days, in light of the broad scope of the amendments proposed in the NPR, the complex and highly-technical nature of the proposed amendments, and the potential impact on industry members. The Commission grants this request, extending the comment period for an additional 90 days, until July 17, 2017.1 Dated: April 11, 2017. Todd A. Stevenson, Secretary, U.S. Consumer Product Safety Commission. [FR Doc. 2017–07556 Filed 4–13–17; 8:45 am] BILLING CODE 6355–01–P ENVIRONMENTAL PROTECTION AGENCY 40 CFR Parts 50 and 58 [EPA–HQ–OAR–2013–0146; FRL–9961–20– OAR] Release of the Policy Assessment for the Review of the Primary National Ambient Air Quality Standards for Oxides of Nitrogen Environmental Protection Agency (EPA). ACTION: Notice of availability. AGENCY: The Environmental Protection Agency (EPA) is announcing the availability of the final document titled Policy Assessment for the Review of the Primary National Ambient Air Quality Standards for Oxides of Nitrogen (NO2 SUMMARY: 1 The Commission voted 4–1 to approve the comment period extension request. Acting Chairman Ann Marie Buerkle, Commissioner Robert S. Adler, Commissioner Marietta S. Robinson and Commissioner Joseph P. Mohorovic voted to approve the extension notice. Commissioner Elliot F. Kaye voted against the extension notice. E:\FR\FM\14APP1.SGM 14APP1

Agencies

[Federal Register Volume 82, Number 71 (Friday, April 14, 2017)]
[Proposed Rules]
[Pages 17945-17947]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-07477]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0164; Directorate Identifier 2017-NE-06-AD]
RIN 2120-AA64


Airworthiness Directives; General Electric Company Turbofan 
Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain General Electric Company (GE) CF34-8 model turbofan engines. 
This proposed AD was prompted by analysis that resulted in the 
reduction of the life of the affected fan blades. This proposed AD 
would require inspections of the affected fan blades until their 
removal. We are proposing this AD to correct the unsafe condition on 
these products.

DATES: We must receive comments on this proposed AD by May 30, 2017.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact General 
Electric Company, GE-Aviation, Room 285, 1 Neumann Way, Cincinnati, OH 
45215, phone: 513-552-3272; fax: 513-552-3329; email: geae.aoc@ge.com. 
You may view this service information at the FAA, Engine & Propeller 
Directorate, 1200 District Avenue, 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 https://www.regulations.gov by searching for and locating Docket No. FAA-2017-
0164; 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 proposed AD, the regulatory evaluation, any comments 
received, and other information. The street 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: Martin Adler, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 1200 
District Avenue, Burlington, MA 01803; phone: 781-238-7157; fax: 781-
238-7199; email: martin.adler@faa.gov.

SUPPLEMENTARY INFORMATION: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this NPRM. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2017-0164; 
Directorate Identifier 2017-NE-06-AD'' at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this NPRM. We will 
consider all comments received by the closing date and may amend this 
NPRM because of those comments.
    We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We learned that GE has determined, based on analysis, that the 
stresses in the pinholes in the affected fan blade could result in 
crack initiation at pinhole surfaces beyond 19,000, 19,500, or 25,000 
cyles-since-new (CSN), depending on the engine model on which the blade 
is installed. GE, therefore, has initiated a program of initial and 
repetitive eddy current inspections (ECIs) and removal of this fan 
blade before it reaches 41,000 CSN. GE also provided an option to 
repair the blade which allows for an additional 28,000 cycles before it 
must be removed. This condition, if not corrected, could result in 
failure of the fan blade, uncontained blade release, damage to the 
engine, and damage to the airplane.

Related Service Information Under 1 CFR Part 51

    We reviewed GE Alert Service Bulletins (ASBs) CF34-8C SB 72-A0137 
R05, dated June 15, 2016; and CF34-8E SB 72-A0060 R05, dated June 15, 
2016. These ASBs provide the procedures necessary for calculating the 
adjusted CSN for the initial inspection. This service information is 
reasonably available because the interested parties have access to it 
through their normal course of business or by the means identified in 
the ADDRESSES section.

Other Related Service Information

    We reviewed GE ASB CF34-8E SB 72-A0115 R03, issued on December 9, 
2016, and GE ASB CF34-8C SB 72-A0225 R03, issued on December 9, 2016. 
The ASB's describe procedures for repairing fan blade, part number (P/
N) 4114T15P02, to P/N 4114T31G01 with the installation of a bushing in 
the pinholes.

FAA's Determination

    We are proposing this AD because we evaluated all the relevant 
information and determined the unsafe condition described previously is 
likely to exist or develop in other products of the same type design.

Proposed AD Requirements

    This proposed AD would require initial and repetitive ECIs of the 
affected fan blade. This proposed AD would also require removal or 
repair of the affected fan blade at a reduced life. A fan blade

[[Page 17946]]

that has been repaired is eligible for an additional 28,000 cycles in 
service before it must be removed.

Differences Between This Proposed AD and the Service Information

    The determination in this proposed AD of CSN, when CSN is not 
known, is simpler and clearer than the method indicated in the service 
information. The service information has several options that may lead 
to confusion among operators in making this determination.

Costs of Compliance

    We estimate that this proposed AD affects 1,986 engines installed 
on airplanes of U.S. registry.
    We estimate the following costs to comply with this proposed AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Initial ECI Inspection................  4 work-hours x $85 per                $0            $340        $675,240
                                         hour = $340.
Replacement of fan blade (prorated      0 work-hours x $85 per             5,460           5,460      10,843,560
 annual cost).                           hour = $0.
----------------------------------------------------------------------------------------------------------------

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

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):

General Electric Company: Docket No. FAA-2017-0164; Directorate 
Identifier 2017-NE-06-AD.

(a) Comments Due Date

    We must receive comments by May 30, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to General Electric Company (GE) CF34-8C1, CF34-
8C5, CF34-8C5A1, CF34-8C5B1, CF34-8C5A2, CF34-8C5A3, CF34-8E2, CF34-
8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E5A2, CF34-8E6 and CF34-8E6A1 
engines, including engines marked on the engine data plate as CF34-
8C5B1/B, CF34-8C5/B, CF34-8C5A1/B, CF34-8C5A2/B, CF34-8C5/M, CF34-
8C5A1/M, CF34-8C5A2/M, CF34-8C5A3/B, or CF34-8C5B1/M, with a fan 
blade, part number (P/N) 4114T15P02 or P/N 4114T31G01, installed.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7230, Turbine Engine 
Compressor Section.

(e) Unsafe Condition

    This AD was prompted by analysis that resulted in the reduction 
of the life of the affected fan blades. We are issuing this AD to 
prevent failure of the fan blade, uncontained blade release, damage 
to the engine, and damage to the airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Eddy Current Inspections (ECIs)

    (1) For CF34-8C1, CF34-8C5B1, CF34-8C5B1/B and CF34-8E2 engines 
with fan blade, P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 25,000 cycles-since-new (CSN); and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter.
    (2) For CF34-8C5, CF34-8C5/B, CF34-8C5A1, CF34-8C5A1/B, CF34-
8C5A2, CF34-8C5A2/B, CF34-8E2A1, CF34-8E5, CF34-8E5A1, CF34-8E6 and 
CF34-8E6A1 engines with fan blade, P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 19,500 CSN; and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter, until the fan blade has accumulated 25,000 CSN, then 
repeat the inspection every 1,500 cycles thereafter.
    (3) For CF34-8C5/M, CF34-8C5A1/M, CF34-8C5A2/M, CF34-8C5A3, 
CF34-8C5A3/B, CF34-8C5B1/M, and CF34-8E5A2 engines with fan blade, 
P/N 4114T15P02, installed:
    (i) Perform an initial ECI of the fan blade pinhole prior to the 
fan blade accumulating 19,000 CSN; and
    (ii) Repeat this inspection within every 3,000 cycles 
thereafter, until the fan blade has accumulated 25,000 CSN, then 
repeat the inspection every 1,500 cycles thereafter.
    (4) For any affected engine with a fan blade, P/N 4114T15P02, 
installed where the CSN of the fan blade is unknown on the effective 
date of this AD:

[[Page 17947]]

    (i) Assume the blade has accumulated 25,000 CSN on the effective 
date of this AD; and
    (ii) Inspect the blade prior to installation or within 500 
cycles after the effective date of this AD, whichever is earlier.
    (5) If a fan blade is moved from one affected engine model to 
another affected model after the initial ECI:
    (i) Perform an additional ECI of the blade prior to installation 
in the new model; and
    (ii) Repeat this inspection based on the intervals of the new 
engine installation, as specified in paragraph (g) of this AD.
    (6) If a fan blade, P/N 4114T15P02, has been used on more than 
one engine model prior to the initial ECI, use Appendix A of GE 
Alert Service Bulletin (ASB) CF34-8C SB 72-A0137 R05, dated June 15, 
2016, or Appendix A of GE ASB CF34-8E SB 72-A0060 R05, dated June 
15, 2016, to calculate the new cycle limit for the initial 
inspection of that fan blade.

(h) Fan Blade Removal

    (1) For any affected engine with a fan blade, P/N 4114T15P02, 
installed, remove the blade from service or repair to P/N 4114T31G01 
prior to the blade accumulating 41,000 CSN.
    (2) For any affected engine with a fan blade, P/N 4114T31G01, 
installed, remove the blade from service prior to the blade 
accumulating 28,000 cycles since installation of the pinhole 
bushing.

(i) 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.

(j) Related Information

    (1) For more information about this AD, contact Martin Adler, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7157; fax: 781-238-7199; email: martin.adler@faa.gov.
    (2) GE ASBs: CF34-8C SB 72-A0137 R05, dated June 15, 2016; CF34-
8E SB 72-A0060 R05, dated June 15, 2016; CF34-8E SB 72A0115 R03, 
issued December 9, 2016; and CF34-8C ASB 72-A0225 R03, issued 
December 9, 2016; can be obtained from GE using the contact 
information in paragraph (j)(3) of this AD.
    (3) For service information identified in this proposed AD, 
contact General Electric Company, GE-Aviation, Room 285, 1 Neumann 
Way, Cincinnati, OH 45215, phone: 513-552-3272; fax: 513-552-3329; 
email: geae.aoc@ge.com.
    (4) You may view this service information at the FAA, Engine & 
Propeller Directorate, 1200 District Avenue, Burlington, MA. For 
information on the availability of this material at the FAA, call 
781-238-7125.

    Issued in Burlington, Massachusetts, on April 5, 2017.
Carlos A. Pestana,
Acting Manager, Engine & Propeller Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-07477 Filed 4-13-17; 8:45 am]
 BILLING CODE 4910-13-P
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