[Federal Register Volume 82, Number 229 (Thursday, November 30, 2017)]
[Rules and Regulations]
[Pages 56723-56725]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-25719]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1044; Product Identifier 2017-NE-38-AD; Amendment 
39-19110; AD 2017-24-06]
RIN 2120-AA64


Airworthiness Directives; CFM International S.A. Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
CFM International S.A. (CFM) LEAP-1A turbofan engines. This AD requires 
removal, inspection, rework, and re-identification of the high-pressure 
turbine (HPT) stage 2 disk, part number (P/N) 2466M52G03. This AD was 
prompted by a quality escape at the manufacturer that resulted in 
cracks appearing during forging of the HPT stage 2 disks. We are 
issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 15, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 15, 
2017.
    We must receive comments on this AD by January 16, 2018.

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.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For service information identified in this final rule, 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: [email protected]. You may view this service 
information at the FAA, Engine and Propeller Standards Branch, 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 http://www.regulations.gov by searching for and locating Docket No. FAA-2017-
1044; 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 final rule, 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: Christopher McGuire, Aerospace 
Engineer, ECO Branch, FAA, 1200 District Avenue, Burlington, MA 01803; 
phone: 781-238-7120; fax: 781-238-7199; email: [email protected].

SUPPLEMENTARY INFORMATION: 

Discussion

    We learned from CFM that there was a quality escape at the 
manufacturer that resulted in cracks appearing during forging of CFM 
LEAP-1A HPT stage 2 disks. This condition, if not corrected, could 
result in failure of the HPT stage 2 disk, uncontained release of the 
disk, damage to the engine, and damage to the airplane. We are issuing 
this AD to correct the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed CFM Service Bulletin (SB) LEAP-1A-72-00-0167-01A-930A-
D, Issue 001, dated September 28, 2017. The SB describes procedures for 
removal, inspection, rework, and re-identification of HPT stage 2 disk, 
P/N 2466M52G03. 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.

FAA's Determination

    We are issuing 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.

AD Requirements

    This AD requires removal, inspection, rework, and re-identification 
of the HPT stage 2 disk, P/N 2466M52G03.

FAA's Justification and Determination of the Effective Date

    An unsafe condition exists that requires the immediate adoption of 
this AD without providing an opportunity for public comments prior to 
adoption. The FAA has found that the risk to the flying public 
justifies waiving notice and comment prior to adoption of this rule 
because the compliance time for the required action is shorter than the 
time necessary for the public to comment and for us to publish the 
final rule. Therefore, we find good cause that notice and opportunity 
for prior public comment are impracticable. In addition, for the reason 
stated above, we find that good cause exists for making this amendment 
effective in less than 30 days.

Comments Invited

    This AD is a final rule that involves requirements affecting flight 
safety and was not preceded by notice and an opportunity for public 
comment. However, we invite you to send any written data, views, or 
arguments about this final rule. Send your comments to an address 
listed under the ADDRESSES section. Include the docket number FAA 2017-
1044 and Product Identifier 2017-NE-38-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory, 
economic, environmental, and energy aspects of this final rule. We will 
consider all comments received by the closing date and may amend this 
final rule 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 final rule.

Costs of Compliance

    We estimate that this AD affects 7 engines installed on airplanes 
of U.S. registry.
    We estimate the following costs to comply with this AD:

[[Page 56724]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on U.S.
                Action                         Labor cost           Parts cost        product        operators
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Remove, inspect, rework, and re-        560 work-hours x $85 per              $0         $47,600        $333,200
 identify HPT stage 2 disk.              hour = $47,600.
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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.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to engines, propellers, and 
associated appliances to the Manager, Engine and Propeller Standards 
Branch, Policy and Innovation Division.

Regulatory Findings

    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 that this AD:
    (1) Is not a ``significant regulatory action'' under Executive 
Order 12866,
    (2) Is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979),
    (3) Will not affect intrastate aviation in Alaska, 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.

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):

2017-24-06 CFM International S.A.: Amendment 39-19110; Docket No. 
FAA-2017-1044; Product Identifier 2017-NE-38-AD.

(a) Effective Date

    This AD is effective December 15, 2017.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International S.A. (CFM) LEAP-1A23, LEAP-
1A24, LEAP-1A24E1, LEAP-1A26, LEAP-1A26E1, LEAP-1A30, LEAP-1A32, 
LEAP-1A33, LEAP-1A33B2 and LEAP-1A35A engines with a high-pressure 
turbine (HPT) stage 2 disk, with a part number (P/N) 2466M52G03 and 
serial number (S/N) listed in Table 1 of CFM Service Bulletin (SB) 
LEAP-1A SB 72-0167-01A-930A-D, Issue 001, dated September 28, 2017, 
installed.

(d) Subject

    Joint Aircraft System Component (JASC)/Air Transport Association 
(ATA) of America Code 7250, Turbine Section.

(e) Unsafe Condition

    This AD was prompted by a quality escape at the manufacturer 
that resulted in cracks appearing during forging of the HPT stage 2 
disks. We are issuing this AD to prevent failure of the HPT stage 2 
disks. The unsafe condition, if not corrected, could result in 
uncontained release of the HPT stage 2 disks, damage to the engine, 
and damage to the airplane.

(f) Compliance

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

(g) Required Actions

    Prior to accumulating 1,200 engine cycles since new after the 
effective date of this AD, remove, inspect, rework, and re-identify 
the HPT stage 2 disk, P/N 2466M52G03, in accordance with the 
Accomplishment Instructions, paragraph 5.B.(2), in CFM SB LEAP-1A-
72-00-0167-01A-930A-D, Issue 001, dated September 28, 2017.

(h) Alternative Methods of Compliance (AMOCs)

    (1) The Manager, ECO Branch, FAA, has the authority to approve 
AMOCs for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the manager of the 
certification office, send it to the attention of the person 
identified in paragraph (i) of this AD. You may email your request 
to: [email protected].
    (2) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

(i) Related Information

    For more information about this AD, contact Chris McGuire, 
Aerospace Engineer, ECO Branch, FAA, 1200 District Avenue, 
Burlington, MA 01803; phone: 781-238-7120; fax: 781-238-7199; email: 
[email protected].

(j) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (i) CFM Service Bulletin LEAP-1A-72-00-0167-01A-930A-D, Issue 
001, dated September 28, 2017.
    (ii) Reserved.
    (3) For CFM 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: [email protected].
    (4) You may view this service information at FAA, Engine and 
Propeller Standards

[[Page 56725]]

Branch, 1200 District Avenue, Burlington, MA. For information on the 
availability of this material at the FAA, call 781-238-7125.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Burlington, Massachusetts, on November 21, 2017.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2017-25719 Filed 11-29-17; 8:45 am]
 BILLING CODE 4910-13-P


