Airworthiness Directives; CFM International S.A. Turbofan Engines

[Federal Register Volume 83, Number 231 (Friday, November 30, 2018)]
[Rules and Regulations]
[Pages 61529-61531]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26026]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0869; Product Identifier 2018-NE-32-AD; Amendment 
39-19435; AD 2018-20-01]
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 all CFM 
International S.A. (CFM) LEAP-1B21, LEAP-1B23, LEAP-1B25, LEAP-1B27, 
LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, LEAP-1B28B2C, LEAP-1B28B3, LEAP-
1B28BBJ1, and LEAP-1B28BBJ2 turbofan engines with a certain high-
pressure turbine (HPT) stator case (HPT cases) installed. This AD 
requires removal of affected HPT cases from service and their 
replacement with a part eligible for installation. This AD was prompted 
by the discovery of a quality escape at a manufacturing facility 
involving unapproved welds on HPT cases. We are issuing this AD to 
address the unsafe condition on these products.

DATES: This AD is effective December 17, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of December 17, 
2018.
    We must receive comments on this AD by January 14, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
    <bullet> Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
    <bullet> Fax: 202-493-2251.
    <bullet> 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.
    <bullet> 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 01803. For information on the 
availability of this material at the FAA, call 781-238-7759. It is also 
available on the internet at http://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-0869.

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-2018-
0869; or in person at Docket Operations 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 Operations (phone: 
800-647-5527) is listed above. 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 of a quality escape at one of their suppliers, 
AECC Aero Science and Technology Co., Ltd., which was performing welds 
on newly-manufactured components to correct errors introduced in their 
manufacturing process. These welds were not reviewed or approved by 
either CFM or the FAA. CFM's review of manufacturing records determined 
that these parts include HPT cases installed on CFM LEAP-1B turbofan 
engines. These HPT cases are life limited. The unapproved repairs 
reduced the material capability of these cases which requires their 
removal prior to reaching their published Airworthiness Limitation 
Section life limit. This condition, if not addressed, could result in 
failure of the HPT case, engine fire, and damage to the airplane. We 
are issuing this AD to address the unsafe condition on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed CFM Service Bulletin (SB) LEAP-1B-72-00-0193-01A-930A-
D, Issue 003, dated November 5, 2018. The SB describes procedures for 
removing the affected HPT cases from the engine. 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 of the affected HPT cases from service and 
their replacement with a part eligible for installation.

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 the 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. Certain HPTs cases must be removed within 200 cycles after 
the effective date of this AD to ensure they do not fail. 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-2018-
0869 and Product Identifier 2018-NE-32-AD at the beginning of your 
comments. We specifically invite comments on the overall regulatory,

[[Page 61530]]

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

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                     Cost per      Cost on  U.S.
                Action                         Labor cost           Parts cost        product        operators
----------------------------------------------------------------------------------------------------------------
Remove HPT case and FPI of forward      1000 work-hour x $85 per        $179,400        $264,400        $528,800
 flange.                                 hour = $85,000.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacements 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
replacement:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace combustion case assembly..............  10 work-hours x $85 per hour =          $558,800        $559,650
                                                 $850.
----------------------------------------------------------------------------------------------------------------

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):

2018-20-01 CFM International S.A.: Amendment 39-19435; Docket No. 
FAA-2018-0869; Product Identifier 2018-NE-32-AD.

(a) Effective Date

    This AD is effective December 17, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International S.A. (CFM) LEAP-1B21, LEAP-
1B23, LEAP-1B25, LEAP-1B27, LEAP-1B28, LEAP-1B28B1, LEAP-1B28B2, 
LEAP-1B28B2C, LEAP-1B28B3, LEAP-1B28BBJ1, and LEAP-1B28BBJ2 turbofan 
engines with a high-pressure turbine (HPT) stator case (HPT case), 
part number (P/N) 2541M81G01 installed, and with any HPT case serial 
number (S/N) listed in Table 1 or Table 2 of Planning Information, 
paragraph 3.A., of CFM Service Bulletin (SB) LEAP-1B-72-00-0193-01A-
930A-D, Issue 003, dated November 5, 2018.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7250, Turbine 
Section.

(e) Unsafe Condition

    This AD was prompted by the discovery of a quality escape at a 
manufacturing facility involving unapproved welds on HPT cases. We 
are issuing this AD to prevent failure of the HPT case. The unsafe 
condition, if not addressed, could result in engine fire and damage 
to the airplane.

[[Page 61531]]

(f) Compliance

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

(g) Required Actions

    (1) After the effective date of this AD, remove the affected HPT 
case from service no later than the number of cycles in service 
specified in Table 1 or Table 2 of Planning Information, paragraph 
3.A., of CFM SB LEAP-1B-72-00-0193-01A-930A-D, Issue 003, dated 
November 5, 2018.
    (2) After removing the HPT case as required in paragraph (g)(1) 
of this AD, and before further flight, determine if the combustor 
diffuser nozzle (CDN) case, P/N 2548M30G01 to 2548M30G07, inclusive, 
and with any CDN case S/N listed in Table 1 or Table 2 of Planning 
Information, paragraph 3.A., of CFM SB LEAP-1B-72-00-0193-01A-930A-
D, Issue 003, dated November 5, 2018, needs to be replaced as 
follows:
    (i) Inspect the HPT case forward flange outer diameter using the 
Accomplishment Instructions, paragraphs 5.B.(1), 5.B.(2), and 
5.B.(4) of CFM SB LEAP-1B-72-00-0193-01A-930A-D, Issue 003, dated 
November 5, 2018.
    (ii) If, during the inspection required by paragraph (g)(2)(i) 
of this AD, you find an HPT case forward flange cracked across the 
full axial length of the outer diameter, remove the CDN case, P/N 
2548M30G01 to 2548M30G07, inclusive, from service and, before 
further flight, replace with a part eligible for installation.

(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 Christopher 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-1B-72-00-0193-01A-930A-D, Issue 
003, dated November 5, 2018.
    (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 Branch, 1200 District Avenue, Burlington, MA 
01803. For information on the availability of this material at the 
FAA, call 781-238-7759.
    (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 26, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-26026 Filed 11-29-18; 8:45 am]
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