Airworthiness Directives; CFM International S.A. Turbofan Engines, 59672-59674 [2015-24729]

Download as PDF 59672 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Proposed Rules 6. Amend § 121.103 to add paragraph (a)(8) to read as follows: ■ § 121.103 How does SBA determine affiliation? (a) * * * (8) For SBA’s Business Loan and Surety Bond Guarantee programs, the size standards and bases for affiliation are set forth in § 121.301. * * * * * ■ 7. Amend § 121.301 to add paragraph (f) to read as follows: § 121.301 What size standards and affiliation principles are applicable to financial assistance programs? asabaliauskas on DSK5VPTVN1PROD with PROPOSALS * * * * * (f) Concerns and entities are affiliates of each other when one controls or has the power to control the other, or a third party or parties controls or has the power to control both. It does not matter whether control is exercised, so long as the power to control exists. For the purposes of SBA’s Business Loan Programs, Disaster Loan Program, and Surety Bond Guarantee Program, the following principles of affiliation apply: (1) Affiliation based on ownership. For determining affiliation based on equity ownership, a concern is an affiliate of an individual, concern, or entity that owns or has the power to control more than 50 percent of the concern’s voting equity. If no individual, concern, or entity is found to control, SBA will deem the Board of Directors or President or Chief Executive Officer (CEO) (or other officers, managing members, or partners who control the management of the concern) to be in control of the concern. (2) Affiliation arising under stock options, convertible securities, and agreements to merge. (i) In determining size, SBA considers stock options, convertible securities, and agreements to merge (including agreements in principle) to have a present effect on the power to control a concern. SBA treats such options, convertible securities, and agreements as though the rights granted have been exercised. (ii) Agreements to open or continue negotiations towards the possibility of a merger or a sale of stock at some later date are not considered ‘‘agreements in principle’’ and are thus not given present effect. (iii) Options, convertible securities, and agreements that are subject to conditions precedent which are incapable of fulfillment, speculative, conjectural, or unenforceable under state or Federal law, or where the probability of the transaction (or exercise of the rights) occurring is VerDate Sep<11>2014 19:21 Oct 01, 2015 Jkt 238001 shown to be extremely remote, are not given present effect. (iv) An individual, concern or other entity that controls one or more other concerns cannot use options, convertible securities, or agreements to appear to terminate such control before actually doing so. SBA will not give present effect to individuals’, concerns’ or other entities’ ability to divest all or part of their ownership interest in order to avoid a finding of affiliation. (3) Affiliation based on common management. Affiliation arises where the CEO or President of the applicant concern (or other officers, managing members, or partners who control the management of the concern) also controls the management of one or more other concerns. Affiliation also arises where a single individual, concern or entity that controls the Board of Directors or management of one concern also controls the Board of Directors or management of one of more other concerns. (4) Affiliation based on identity of interest. (i) Affiliation may arise among two or more persons (including any individual, concern, or other entity) with an identity of interest. An individual, concern, or entity may rebut a determination of identity of interest with evidence showing that the interests deemed to be one are in fact separate. (ii) SBA may presume an identity of interest between close relatives, as defined in 13 CFR 120.10, with identical or substantially identical business or economic interests (such as where the family members operate concerns in the same or similar industry in the same geographic area). (5) Affiliation based on franchise and license agreements. The restraints imposed on a franchisee or licensee by its franchise or license agreement relating to standardized quality, advertising, accounting format and other similar provisions, generally will not be considered in determining whether the franchisor or licensor is affiliated with an applicant franchisee or licensee provided the applicant franchisee or licensee has the right to profit from its efforts and bears the risk of loss commensurate with ownership. Affiliation may arise however, through other means, such as common ownership, common management or excessive restrictions upon the sale of the franchise interest. (6) Affiliation based on SBA’s determination of the totality of the circumstances. SBA may find affiliation after considering the totality of the circumstances, even when no single factor is sufficient to constitute affiliation. PO 00000 Frm 00006 Fmt 4702 Sfmt 4702 (7) Determining the concern’s size. In determining the concern’s size, SBA counts the receipts, employees, or the alternate size standard of the concern whose size is at issue and all of its domestic and foreign affiliates, regardless of whether the affiliates are organized for profit. (8) Exceptions to affiliation. For exceptions to affiliation, see 13 CFR 121.103(b). Maria Contreras-Sweet, Administrator. [FR Doc. 2015–25204 Filed 10–1–15; 8:45 am] BILLING CODE 8025–01–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2015–2983; Directorate Identifier 2015–NE–20–AD] RIN 2120–AA64 Airworthiness Directives; CFM International S.A. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: We propose to adopt a new airworthiness directive (AD) for certain CFM International S.A. (CFM) CFM56– 5B series turbofan engines. This proposed AD was prompted by a corrected lifing analysis by the engine manufacturer that shows the need to identify an initial and repetitive inspection threshold for certain part number (P/N) turbine rear frames (TRFs). This proposed AD would require initial and repetitive inspections of certain P/N TRFs on the low-pressure turbine (LPT) frame assembly. We are proposing this AD to prevent failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. DATES: We must receive comments on this proposed AD by December 1, 2015. 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 http://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. SUMMARY: E:\FR\FM\02OCP1.SGM 02OCP1 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Proposed Rules • 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 proposed AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877– 432–3272; fax: 877–432–3329; email: aviation.fleetsupport@ge.com. 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– 2983; 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. Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7183; fax: 781–238– 7199; email: kyle.gustafson@faa.gov. FOR FURTHER INFORMATION CONTACT: SUPPLEMENTARY INFORMATION: asabaliauskas on DSK5VPTVN1PROD with PROPOSALS Comments Invited We invite you to send any written relevant data, views, or arguments about this proposal. Send your comments to an address listed under the ADDRESSES section. Include ‘‘Docket No. FAA– 2015–2983; Directorate Identifier 2015– NE–20–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 because of 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 we receive about this proposed AD. VerDate Sep<11>2014 19:21 Oct 01, 2015 Jkt 238001 59673 Discussion We were informed by CFM that it has corrected its lifing analysis for the TRF, P/N 338–102–907–0 and P/N 338–102– 908–0, on the LPT frame assembly installed on CFM56–5B turbofan engines. This corrected lifing analysis shows the need for initial and repetitive inspections of certain P/N TRFs to manage low-cycle fatigue cracks. This condition, if not corrected, could result in failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. The initial and repetitive inspection intervals differ depending on whether CFM Service Bulletin (SB) No. CFM56– 5B S/B 72–0308, Revision 5, dated October 12, 2007, has been applied. We are proposing to allow engines with TRFs that have exceeded the initial inspection threshold a continued inservice allowance of 150 cycles to provide sufficient time to perform the initial inspection. The proposed repetitive inspection intervals are based on the size of the crack, if any, found during the inspection. cost of this proposed AD on U.S. operators to be $23,970. Relevant Service Information Under 1 CFR Part 51 We reviewed CFM SB No. CFM56–5B S/B 72–0850, dated December 19, 2012, and CFM SB No. CFM56–5B S/B 72– 0308, Revision 5, dated October 12, 2007. CFM SB No. CFM56–5B S/B 72– 0850 describes procedures for inspecting the TRF. CFM SB No. CFM56–5B S/B 72–0308 identifies the engines to which this proposed AD applies. 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 of this document. 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. 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 inspections of the TRF on the LPT frame assembly. Costs of Compliance We estimate that this proposed AD would affect about 94 engines installed on airplanes of U.S. registry. We also estimate that it would take about 3 hours per engine to do the inspection. The average labor rate is $85 per hour. Based on these figures, we estimate the PO 00000 Frm 00007 Fmt 4702 Sfmt 4702 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 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: E:\FR\FM\02OCP1.SGM 02OCP1 59674 Federal Register / Vol. 80, No. 191 / Friday, October 2, 2015 / Proposed Rules 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): ■ CFM International S.A.: Docket No. FAA– 2015–2983; Directorate Identifier 2015– NE–20–AD. (a) Comments Due Date We must receive comments by December 1, 2015. (b) Affected ADs None. (c) Applicability This AD applies to CFM International S.A. (CFM) CFM56–5B engines with turbine rear frame (TRF), part number (P/N) 338–102– 907–0 or P/N 338–102–908–0, installed. asabaliauskas on DSK5VPTVN1PROD with PROPOSALS (d) Unsafe Condition This AD was prompted by a corrected lifing analysis by the engine manufacturer that shows the need for an initial and repetitive inspection of certain P/N TRFs on the low-pressure turbine (LPT) frame assembly. We are issuing this AD to prevent failure of the TRF on the LPT frame assembly, which could lead to engine separation, damage to the engine, and damage to the airplane. (e) Compliance Comply with this AD within the compliance times specified, unless already done. (1) For Engines that have Applied CFM Service Bulletin (SB) No. CFM56–5B S/B 72– 0308: (i) Prior to accumulating 25,000 cycles since new (CSN) on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial eddy current inspection (ECI) or a fluorescent penetrant inspection (FPI) of the TRF mount struts on the LPT assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 cycles-in-service after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56–5B S/B 72–0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56–5B S/B 72–0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, or the cumulative length of all cracks at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 1,670 cycles since last inspection (CSLI). VerDate Sep<11>2014 19:21 Oct 01, 2015 Jkt 238001 (v) If the cumulative length of cracks at any TRF mount strut location is greater than or equal to 0.20 inches, but less than 0.25 inches, repeat the inspection within 280 CSLI. (vi) If the cumulative length of cracks at any TRF mount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (2) For Engines that have Not Applied CFM SB No. CFM56–5B S/B 72–0308: (i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame assembly or within 150 cycles after the effective date of this AD, whichever occurs later, perform an initial ECI or FPI of the TRF mount struts on the LPT frame assembly. (ii) For engines with unknown CSN on the TRF of the LPT frame assembly, perform the initial inspection required by this AD within 150 cycles-in-service after the effective date of this AD. (iii) Use paragraph 3.B. in the Accomplishment Instructions of CFM SB No. CFM56–5B S/B 72–0850, dated December 19, 2012, to do the ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB No. CFM56–5B S/B 72–0850, to do the FPI. Do not include TRF mount strut crack lengths towards the cumulative crack length after the cracks are repaired. (iv) If no cracks are found on any of the three TRF mount struts, or the cumulative length of cracks at any TRF mount strut location is less than 0.20 inches, repeat the inspection within 2,500 CSLI. (v) If the cumulative length of cracks at any TRF mount strut location is greater than or equal to 0.20 inches and less than 0.25 inches, repeat the inspection within 370 CSLI. (vi) If the cumulative length of cracks at any TRF mount strut location is 0.25 inches or greater, replace the TRF with a part eligible for installation before further flight. (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 Kyle Gustafson, Aerospace Engineer, Engine Certification Office, FAA, Engine & Propeller Directorate, 12 New England Executive Park, Burlington, MA 01803; phone: 781–238–7183; fax: 781–238–7199; email: kyle.gustafson@faa.gov. (2) CFM SB No. CFM56–5B S/B 72–0850, dated December 19, 2012, and CFM SB No. CFM56–5B S/B 72–0308, Revision 5, dated October 12, 2007, can be obtained from CFM using the contact information in paragraph (g)(3) of this proposed AD. (3) For service information identified in this AD, contact CFM International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 285, Cincinnati, OH 45125; phone: 877–432–3272; fax: 877–432–3329; email: aviation.fleetsupport@ge.com. (4) You may view this service information at the FAA, Engine & Propeller Directorate, PO 00000 Frm 00008 Fmt 4702 Sfmt 4702 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 September 24, 2015. Colleen M. D’Allesandro, Directorate Manager, Engine & Propeller Directorate, Aircraft Certification Service. [FR Doc. 2015–24729 Filed 10–1–15; 8:45 am] BILLING CODE 4910–13–P DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 147 [Docket No. FAA–2015–3901; Notice No. 15–10] RIN 2120–AK48 Aviation Maintenance Technician Schools Federal Aviation Administration (FAA), DOT. ACTION: Notice of proposed rulemaking (NPRM). AGENCY: The FAA proposes to amend the regulations governing the curriculum and operations of FAAcertificated Aviation Maintenance Technician Schools. These amendments would modernize and reorganize the required curriculum subjects in the appendices of the current regulations. They would also remove the course content items currently located in the appendices and require that they be placed in each school’s operations specifications so they could more easily be amended when necessary. The amendments are needed because the existing curriculums are outdated, do not meet current industry needs, and can be changed only through notice and comment rulemaking. These amendments would ensure that aviation maintenance technician students receive up-to-date foundational training to meet the demanding and consistently changing needs of the aviation industry. DATES: Send comments on or before December 31, 2015. ADDRESSES: Send comments identified by docket number FAA–2015–3901 using any of the following methods: • Federal Rulemaking Portal: Go to http://www.regulations.gov and follow the online instructions for sending your comments electronically. • Mail: Send comments to Docket Operations, M–30; U.S. Department of Transportation (DOT), 1200 New Jersey Avenue SE., Room W12–140, West Building Ground Floor, Washington, DC 20590–0001. SUMMARY: E:\FR\FM\02OCP1.SGM 02OCP1

Agencies

[Federal Register Volume 80, Number 191 (Friday, October 2, 2015)]
[Proposed Rules]
[Pages 59672-59674]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-24729]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2983; Directorate Identifier 2015-NE-20-AD]
RIN 2120-AA64


Airworthiness Directives; CFM International S.A. 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 CFM International S.A. (CFM) CFM56-5B series turbofan engines. 
This proposed AD was prompted by a corrected lifing analysis by the 
engine manufacturer that shows the need to identify an initial and 
repetitive inspection threshold for certain part number (P/N) turbine 
rear frames (TRFs). This proposed AD would require initial and 
repetitive inspections of certain P/N TRFs on the low-pressure turbine 
(LPT) frame assembly. We are proposing this AD to prevent failure of 
the TRF on the LPT frame assembly, which could lead to engine 
separation, damage to the engine, and damage to the airplane.

DATES: We must receive comments on this proposed AD by December 1, 
2015.

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 http://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.

[[Page 59673]]

     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 proposed AD, contact CFM 
International Inc., Aviation Operations Center, 1 Neumann Way, M/D Room 
285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-432-3329; 
email: aviation.fleetsupport@ge.com. 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-
2983; 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: Kyle Gustafson, Aerospace Engineer, 
Engine Certification Office, FAA, Engine & Propeller Directorate, 12 
New England Executive Park, Burlington, MA 01803; phone: 781-238-7183; 
fax: 781-238-7199; email: kyle.gustafson@faa.gov.

SUPPLEMENTARY INFORMATION:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2015-2983; 
Directorate Identifier 2015-NE-20-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 because of 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 we 
receive about this proposed AD.

Discussion

    We were informed by CFM that it has corrected its lifing analysis 
for the TRF, P/N 338-102-907-0 and P/N 338-102-908-0, on the LPT frame 
assembly installed on CFM56-5B turbofan engines. This corrected lifing 
analysis shows the need for initial and repetitive inspections of 
certain P/N TRFs to manage low-cycle fatigue cracks. This condition, if 
not corrected, could result in failure of the TRF on the LPT frame 
assembly, which could lead to engine separation, damage to the engine, 
and damage to the airplane.
    The initial and repetitive inspection intervals differ depending on 
whether CFM Service Bulletin (SB) No. CFM56-5B S/B 72-0308, Revision 5, 
dated October 12, 2007, has been applied. We are proposing to allow 
engines with TRFs that have exceeded the initial inspection threshold a 
continued in-service allowance of 150 cycles to provide sufficient time 
to perform the initial inspection. The proposed repetitive inspection 
intervals are based on the size of the crack, if any, found during the 
inspection.

Relevant Service Information Under 1 CFR Part 51

    We reviewed CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 
2012, and CFM SB No. CFM56-5B S/B 72-0308, Revision 5, dated October 
12, 2007. CFM SB No. CFM56-5B S/B 72-0850 describes procedures for 
inspecting the TRF. CFM SB No. CFM56-5B S/B 72-0308 identifies the 
engines to which this proposed AD applies. 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 of this document.

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 inspections 
of the TRF on the LPT frame assembly.

Costs of Compliance

    We estimate that this proposed AD would affect about 94 engines 
installed on airplanes of U.S. registry. We also estimate that it would 
take about 3 hours per engine to do the inspection. The average labor 
rate is $85 per hour. Based on these figures, we estimate the cost of 
this proposed AD on U.S. operators to be $23,970.

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:

[[Page 59674]]

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):

CFM International S.A.: Docket No. FAA-2015-2983; Directorate 
Identifier 2015-NE-20-AD.

(a) Comments Due Date

    We must receive comments by December 1, 2015.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International S.A. (CFM) CFM56-5B engines 
with turbine rear frame (TRF), part number (P/N) 338-102-907-0 or P/
N 338-102-908-0, installed.

(d) Unsafe Condition

    This AD was prompted by a corrected lifing analysis by the 
engine manufacturer that shows the need for an initial and 
repetitive inspection of certain P/N TRFs on the low-pressure 
turbine (LPT) frame assembly. We are issuing this AD to prevent 
failure of the TRF on the LPT frame assembly, which could lead to 
engine separation, damage to the engine, and damage to the airplane.

(e) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.
    (1) For Engines that have Applied CFM Service Bulletin (SB) No. 
CFM56-5B S/B 72-0308:
    (i) Prior to accumulating 25,000 cycles since new (CSN) on the 
TRF of the LPT frame assembly or within 150 cycles after the 
effective date of this AD, whichever occurs later, perform an 
initial eddy current inspection (ECI) or a fluorescent penetrant 
inspection (FPI) of the TRF mount struts on the LPT assembly.
    (ii) For engines with unknown CSN on the TRF of the LPT frame 
assembly, perform the initial inspection required by this AD within 
150 cycles-in-service after the effective date of this AD.
    (iii) Use paragraph 3.B. in the Accomplishment Instructions of 
CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the 
ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB 
No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount 
strut crack lengths towards the cumulative crack length after the 
cracks are repaired.
    (iv) If no cracks are found on any of the three TRF mount 
struts, or the cumulative length of all cracks at any TRF mount 
strut location is less than 0.20 inches, repeat the inspection 
within 1,670 cycles since last inspection (CSLI).
    (v) If the cumulative length of cracks at any TRF mount strut 
location is greater than or equal to 0.20 inches, but less than 0.25 
inches, repeat the inspection within 280 CSLI.
    (vi) If the cumulative length of cracks at any TRF mount strut 
location is 0.25 inches or greater, replace the TRF with a part 
eligible for installation before further flight.
    (2) For Engines that have Not Applied CFM SB No. CFM56-5B S/B 
72-0308:
    (i) Prior to accumulating 32,000 CSN on the TRF of the LPT frame 
assembly or within 150 cycles after the effective date of this AD, 
whichever occurs later, perform an initial ECI or FPI of the TRF 
mount struts on the LPT frame assembly.
    (ii) For engines with unknown CSN on the TRF of the LPT frame 
assembly, perform the initial inspection required by this AD within 
150 cycles-in-service after the effective date of this AD.
    (iii) Use paragraph 3.B. in the Accomplishment Instructions of 
CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, to do the 
ECI and paragraph 3.C. in the Accomplishment Instructions of CFM SB 
No. CFM56-5B S/B 72-0850, to do the FPI. Do not include TRF mount 
strut crack lengths towards the cumulative crack length after the 
cracks are repaired.
    (iv) If no cracks are found on any of the three TRF mount 
struts, or the cumulative length of cracks at any TRF mount strut 
location is less than 0.20 inches, repeat the inspection within 
2,500 CSLI.
    (v) If the cumulative length of cracks at any TRF mount strut 
location is greater than or equal to 0.20 inches and less than 0.25 
inches, repeat the inspection within 370 CSLI.
    (vi) If the cumulative length of cracks at any TRF mount strut 
location is 0.25 inches or greater, replace the TRF with a part 
eligible for installation before further flight.

(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 Kyle Gustafson, 
Aerospace Engineer, Engine Certification Office, FAA, Engine & 
Propeller Directorate, 12 New England Executive Park, Burlington, MA 
01803; phone: 781-238-7183; fax: 781-238-7199; email: 
kyle.gustafson@faa.gov.
    (2) CFM SB No. CFM56-5B S/B 72-0850, dated December 19, 2012, 
and CFM SB No. CFM56-5B S/B 72-0308, Revision 5, dated October 12, 
2007, can be obtained from CFM using the contact information in 
paragraph (g)(3) of this proposed AD.
    (3) For service information identified in this AD, contact CFM 
International Inc., Aviation Operations Center, 1 Neumann Way, M/D 
Room 285, Cincinnati, OH 45125; phone: 877-432-3272; fax: 877-432-
3329; email: aviation.fleetsupport@ge.com.
    (4) 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 September 24, 2015.
Colleen M. D'Allesandro,
Directorate Manager, Engine & Propeller Directorate, Aircraft 
Certification Service.
[FR Doc. 2015-24729 Filed 10-1-15; 8:45 am]
 BILLING CODE 4910-13-P