Airworthiness Directives; CFM International S.A. Turbofan Engines, 63559-63561 [2018-26611]

Download as PDF 63559 Rules and Regulations Federal Register Vol. 83, No. 237 Tuesday, December 11, 2018 This section of the FEDERAL REGISTER contains regulatory documents having general applicability and legal effect, most of which are keyed to and codified in the Code of Federal Regulations, which is published under 50 titles pursuant to 44 U.S.C. 1510. The Code of Federal Regulations is sold by the Superintendent of Documents. DEPARTMENT OF TRANSPORTATION Federal Aviation Administration 14 CFR Part 39 [Docket No. FAA–2018–1023; Product Identifier 2018–NE–37–AD; Amendment 39– 19520; AD 2018–25–09] RIN 2120–AA64 Airworthiness Directives; CFM International S.A. Turbofan Engines Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. AGENCY: We are adopting a new airworthiness directive (AD) for all CFM International S.A. (CFM) LEAP–1B21, –1B23, –1B25, –1B27, –1B28, –1B28B1, –1B28B2, –1B28B2C, –1B28B3, –1B28BBJ1, and –1B28BBJ2 turbofan engines. This AD requires removing certain electronic engine control (EEC) system operation (OPS) and engine health monitoring (EHM) software and installing versions eligible for installation. This AD was prompted by six aborted takeoffs on the similarly designed CFM LEAP–1A model turbofan engine after those engines did not advance to the desired takeoff fan speed due to icing in the pressure sensor line. We are issuing this AD to address the unsafe condition on these products. SUMMARY: This AD is effective December 26, 2018. We must receive comments on this AD by January 25, 2019. 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, amozie on DSK3GDR082PROD with RULES DATES: VerDate Sep<11>2014 16:17 Dec 10, 2018 Jkt 247001 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: aviation.fleetsupport@ge.com. 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 https:// www.regulations.gov by searching for and locating Docket No. FAA–2018– 1023. 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–2018– 1023; 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: chris.mcguire@faa.gov. SUPPLEMENTARY INFORMATION: Discussion We received reports of six aborted takeoffs on the similarly designed CFM LEAP–1A model turbofan engine that occurred after those engines did not advance to the desired takeoff fan speed. While we have not received any reports of aborted takeoffs with the CFM LEAP– 1B model turbofan engine, the unsafe condition is likely to exist because of PO 00000 Frm 00001 Fmt 4700 Sfmt 4700 similarities in design and instances of ice and moisture found in the pressure sense subsystem lines. The aborted takeoffs happened on the first takeoff of the day after the airplane was exposed to sub-freezing temperatures for more than six hours. After further investigation, the operator found water and ice in the pressure sensor lines, which prevented the pressure sensor from accurately measuring the pressure. As a result, CFM improved the EEC OPS and EHM software to detect and accommodate pressure sensor line freezing. This condition, if not addressed, could result in icing in the pressure sensor lines, inaccurate pressure sensor readings, failure of one or more engines, loss of thrust control, and loss of the airplane. We are issuing this AD to address the unsafe condition on these products. Related Service Information We reviewed CFM Service Bulletin (SB) LEAP–1B–73–00–0016–01A– 930A–D, Issue 002, dated October 30, 2018. The SB introduces new EEC OPS and EHM software and describes procedures for replacing the software. 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 removing certain EEC OPS and EHM software and installing software that is eligible for installation. Differences Between the AD and the Service Information CFM SB LEAP–1B–73–00–0016–01A– 930A–D, Issue 002, dated October 30, 2018, recommends that you install the new EEC OPS and EHM software. This AD requires that you install the new EEC OPS and EHM software, and prohibits the use of earlier EEC OPS and EHM software versions. Interim Action We consider this AD interim action. CFM is developing a modification that will address the unsafe condition identified in this AD. Once this modification is developed, approved, E:\FR\FM\11DER1.SGM 11DER1 63560 Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations and available, we might consider additional rulemaking. 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. The software must be removed and replaced within 60 days to ensure that icing does not develop in the pressure sensor lines on the affected engines. Therefore, we find good cause that notice and opportunity for prior public comment are impracticable. In addition, for the reasons 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–2018–1023 and Product Identifier 2018–NE–37–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 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 final rule. Costs of Compliance We estimate that this AD affects 100 engines installed on airplanes of U.S. registry. We estimate the following costs to comply with this AD: ESTIMATED COSTS Action Labor cost Software removal and software installation .... 1 work-hour × $85 per hour = $85 ................. amozie on DSK3GDR082PROD with RULES 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. VerDate Sep<11>2014 16:17 Dec 10, 2018 Jkt 247001 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 1. The authority citation for part 39 continues to read as follows: ■ PO 00000 Frm 00002 Fmt 4700 Sfmt 4700 Cost per product Parts cost $0 $85 Cost on U.S. operators $8,500 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): ■ 2018–25–09 CFM International S.A.: Amendment 39–19520; Docket No. FAA–2018–1023; Product Identifier 2018–NE–37–AD. (a) Effective Date This AD is effective December 26, 2018. (b) Affected ADs None. (c) Applicability This AD applies to all CFM International S.A. (CFM) LEAP–1B21, –1B23, –1B25, –1B27, –1B28, –1B28B1, –1B28B2, –1B28B2C, –1B28B3, –1B28BBJ1, and –1B28BBJ2 turbofan engines. (d) Subject Joint Aircraft System Component (JASC) Code 7600, Engine Controls. (e) Unsafe Condition This AD was prompted by aborted takeoffs on the similarly designed CFM LEAP–1A model turbofan engine after those engines did not advance to the desired takeoff fan speed due to icing in the pressure sensor line. While we have not received any reports of aborted takeoffs with the CFM LEAP–1B model engine, the unsafe condition is likely to exist because of similarities in design and instances of ice and moisture found in the pressure sense subsystem lines. We are issuing this AD to prevent icing in the pressure sensor lines and inaccurate pressure sensor readings. The unsafe condition, if not addressed, could result in failure of one or E:\FR\FM\11DER1.SGM 11DER1 Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / Rules and Regulations more engines, loss of thrust control, and loss of the airplane. Federal Aviation Administration (f) Compliance Comply with this AD within the compliance times specified, unless already done. 14 CFR Part 39 [Docket No. FAA–2018–0960; Product Identifier 2018–NM–151–AD; Amendment 39–19512; AD 2018–23–51] (g) Required Actions (1) Within 60 days after the effective date of this AD, remove electronic engine control (EEC) system operation (OPS) software, P/N 2628M86P10 or earlier; and engine health monitoring (EHM) software, P/N 2628M87P10 or earlier, from the engine and from service. (2) Before further flight after the removal of the EEC OPS and EHM software required by paragraph (g)(1) of this AD, install EEC OPS and EHM software that is eligible for installation. RIN 2120–AA64 (h) Installation Prohibition AGENCY: After 60 days from the effective date of this AD, do not operate any engine identified in paragraph (c) of this AD with EEC OPS software, P/N 2628M86P10 or earlier, installed; or EHM software, P/N 2628M87P10 or earlier, installed. (i) 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 (j) of this AD. You may email your request to: ANE-AD-AMOC@ faa.gov. (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. (j) 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: chris.mcguire@faa.gov. (k) Material Incorporated by Reference None. amozie on DSK3GDR082PROD with RULES DEPARTMENT OF TRANSPORTATION Issued in Burlington, Massachusetts, on December 3, 2018. Robert J. Ganley, Manager, Engine and Propeller Standards Branch, Aircraft Certification Service. [FR Doc. 2018–26611 Filed 12–10–18; 8:45 am] BILLING CODE 4910–13–P VerDate Sep<11>2014 16:17 Dec 10, 2018 Jkt 247001 Airworthiness Directives; The Boeing Company Airplanes Editorial Note: Rule document 2018–26365 was originally published on pages 62697 through 62700 in the issue of Thursday, December 6, 2018. In that publication, on page 62700, in Figure 2 to paragraph (h), the last sentence in the table was inadvertently truncated. The corrected document is published here in its entirety. Federal Aviation Administration (FAA), DOT. ACTION: Final rule; request for comments. We are adopting a new airworthiness directive (AD) for all The Boeing Company Model 737–8 and –9 airplanes. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This AD requires revising certificate limitations and operating procedures of the airplane flight manual (AFM) to provide the flight crew with runaway horizontal stabilizer trim procedures to follow under certain conditions. This AD was prompted by analysis performed by the manufacturer showing that if an erroneously high single angle of attack (AOA) sensor input is received by the flight control system, there is a potential for repeated nose-down trim commands of the horizontal stabilizer. We are issuing this AD to address the unsafe condition on these products. DATES: This AD is effective December 21, 2018 to all persons except those persons to whom it was made immediately effective by Emergency AD 2018–23–51, issued on November 7, 2018, which contained the requirements of this amendment. We must receive comments on this AD by January 22, 2019. 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. SUMMARY: PO 00000 Frm 00003 Fmt 4700 Sfmt 4700 63561 • Hand Delivery: Deliver to Mail address above between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. 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–2018– 0960; 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 Docket Operations (phone: 800–647– 5527) is in the ADDRESSES section. Comments will be available in the AD docket shortly after receipt. FOR FURTHER INFORMATION CONTACT: Douglas Tsuji, Senior Aerospace Engineer, Systems and Equipment Section, FAA, Seattle ACO Branch, 2200 South 216th St., Des Moines, WA 98198; phone and fax: 206–231–3548; email: Douglas.Tsuji@faa.gov. SUPPLEMENTARY INFORMATION: Discussion On November 7, 2018, we issued Emergency AD 2018–23–51, which requires revising certificate limitations and operating procedures of the AFM to provide the flight crew with runaway horizontal stabilizer trim procedures to follow under certain conditions. This emergency AD was sent previously to all known U.S. owners and operators of these airplanes. This action was prompted by analysis performed by the manufacturer showing that if an erroneously high single AOA sensor input is received by the flight control system, there is a potential for repeated nose-down trim commands of the horizontal stabilizer. This condition, if not addressed, could cause the flight crew to have difficulty controlling the airplane, and lead to excessive nosedown attitude, significant altitude loss, and possible impact with terrain. 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 revising certificate limitations and operating procedures of the AFM to provide the flight crew with runaway horizontal stabilizer trim procedures to follow under certain conditions. E:\FR\FM\11DER1.SGM 11DER1

Agencies

[Federal Register Volume 83, Number 237 (Tuesday, December 11, 2018)]
[Rules and Regulations]
[Pages 63559-63561]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-26611]



========================================================================
Rules and Regulations
                                                Federal Register
________________________________________________________________________

This section of the FEDERAL REGISTER contains regulatory documents 
having general applicability and legal effect, most of which are keyed 
to and codified in the Code of Federal Regulations, which is published 
under 50 titles pursuant to 44 U.S.C. 1510.

The Code of Federal Regulations is sold by the Superintendent of Documents. 

========================================================================


Federal Register / Vol. 83, No. 237 / Tuesday, December 11, 2018 / 
Rules and Regulations

[[Page 63559]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-1023; Product Identifier 2018-NE-37-AD; Amendment 
39-19520; AD 2018-25-09]
RIN 2120-AA64


Airworthiness Directives; CFM International S.A. Turbofan Engines

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Final rule; request for comments.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for all CFM 
International S.A. (CFM) LEAP-1B21, -1B23, -1B25, -1B27, -1B28, -
1B28B1, -1B28B2, -1B28B2C, -1B28B3, -1B28BBJ1, and -1B28BBJ2 turbofan 
engines. This AD requires removing certain electronic engine control 
(EEC) system operation (OPS) and engine health monitoring (EHM) 
software and installing versions eligible for installation. This AD was 
prompted by six aborted takeoffs on the similarly designed CFM LEAP-1A 
model turbofan engine after those engines did not advance to the 
desired takeoff fan speed due to icing in the pressure sensor line. We 
are issuing this AD to address the unsafe condition on these products.

DATES: This AD is effective December 26, 2018.
    We must receive comments on this AD by January 25, 2019.

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: 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 https://www.regulations.gov by searching 
for and locating Docket No. FAA-2018-1023.

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-2018-
1023; 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 received reports of six aborted takeoffs on the similarly 
designed CFM LEAP-1A model turbofan engine that occurred after those 
engines did not advance to the desired takeoff fan speed. While we have 
not received any reports of aborted takeoffs with the CFM LEAP-1B model 
turbofan engine, the unsafe condition is likely to exist because of 
similarities in design and instances of ice and moisture found in the 
pressure sense subsystem lines. The aborted takeoffs happened on the 
first takeoff of the day after the airplane was exposed to sub-freezing 
temperatures for more than six hours. After further investigation, the 
operator found water and ice in the pressure sensor lines, which 
prevented the pressure sensor from accurately measuring the pressure. 
As a result, CFM improved the EEC OPS and EHM software to detect and 
accommodate pressure sensor line freezing. This condition, if not 
addressed, could result in icing in the pressure sensor lines, 
inaccurate pressure sensor readings, failure of one or more engines, 
loss of thrust control, and loss of the airplane. We are issuing this 
AD to address the unsafe condition on these products.

Related Service Information

    We reviewed CFM Service Bulletin (SB) LEAP-1B-73-00-0016-01A-930A-
D, Issue 002, dated October 30, 2018. The SB introduces new EEC OPS and 
EHM software and describes procedures for replacing the software.

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 removing certain EEC OPS and EHM software and 
installing software that is eligible for installation.

Differences Between the AD and the Service Information

    CFM SB LEAP-1B-73-00-0016-01A-930A-D, Issue 002, dated October 30, 
2018, recommends that you install the new EEC OPS and EHM software. 
This AD requires that you install the new EEC OPS and EHM software, and 
prohibits the use of earlier EEC OPS and EHM software versions.

Interim Action

    We consider this AD interim action. CFM is developing a 
modification that will address the unsafe condition identified in this 
AD. Once this modification is developed, approved,

[[Page 63560]]

and available, we might consider additional rulemaking.

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. The software must be removed and replaced within 60 days to 
ensure that icing does not develop in the pressure sensor lines on the 
affected engines. Therefore, we find good cause that notice and 
opportunity for prior public comment are impracticable. In addition, 
for the reasons 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-
1023 and Product Identifier 2018-NE-37-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 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 final rule.

Costs of Compliance

    We estimate that this AD affects 100 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
----------------------------------------------------------------------------------------------------------------
Software removal and software           1 work-hour x $85 per                 $0             $85          $8,500
 installation.                           hour = $85.
----------------------------------------------------------------------------------------------------------------

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):

2018-25-09 CFM International S.A.: Amendment 39-19520; Docket No. 
FAA-2018-1023; Product Identifier 2018-NE-37-AD.

(a) Effective Date

    This AD is effective December 26, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to all CFM International S.A. (CFM) LEAP-1B21, -
1B23, -1B25, -1B27, -1B28, -1B28B1, -1B28B2, -1B28B2C, -1B28B3, -
1B28BBJ1, and -1B28BBJ2 turbofan engines.

(d) Subject

    Joint Aircraft System Component (JASC) Code 7600, Engine 
Controls.

(e) Unsafe Condition

    This AD was prompted by aborted takeoffs on the similarly 
designed CFM LEAP-1A model turbofan engine after those engines did 
not advance to the desired takeoff fan speed due to icing in the 
pressure sensor line. While we have not received any reports of 
aborted takeoffs with the CFM LEAP-1B model engine, the unsafe 
condition is likely to exist because of similarities in design and 
instances of ice and moisture found in the pressure sense subsystem 
lines. We are issuing this AD to prevent icing in the pressure 
sensor lines and inaccurate pressure sensor readings. The unsafe 
condition, if not addressed, could result in failure of one or

[[Page 63561]]

more engines, loss of thrust control, and loss of the airplane.

(f) Compliance

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

(g) Required Actions

    (1) Within 60 days after the effective date of this AD, remove 
electronic engine control (EEC) system operation (OPS) software, P/N 
2628M86P10 or earlier; and engine health monitoring (EHM) software, 
P/N 2628M87P10 or earlier, from the engine and from service.
    (2) Before further flight after the removal of the EEC OPS and 
EHM software required by paragraph (g)(1) of this AD, install EEC 
OPS and EHM software that is eligible for installation.

(h) Installation Prohibition

    After 60 days from the effective date of this AD, do not operate 
any engine identified in paragraph (c) of this AD with EEC OPS 
software, P/N 2628M86P10 or earlier, installed; or EHM software, P/N 
2628M87P10 or earlier, installed.

(i) 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 (j) 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.

(j) 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].

(k) Material Incorporated by Reference

    None.

    Issued in Burlington, Massachusetts, on December 3, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-26611 Filed 12-10-18; 8:45 am]
 BILLING CODE 4910-13-P
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