[Federal Register Volume 83, Number 85 (Wednesday, May 2, 2018)]
[Rules and Regulations]
[Pages 19176-19179]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-09338]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0380; Product Identifier 2018-NE-14-AD; Amendment 
39-19267; AD 2018-09-10]
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) Model CFM56-7B engines. This AD requires 
initial and repetitive inspections of the concave and convex sides of 
the fan blade dovetail to detect cracking and replacement of any blades 
found cracked. This AD was prompted by a recent engine failure due to a 
fractured fan blade, that resulted in the engine inlet cowl 
disintegrating and debris penetrating the fuselage, causing a loss of 
pressurization, and prompting an emergency descent. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective May 14, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of May 14, 
2018.
    We must receive comments on this AD by June 18, 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 781-238-7759. It is also available on 
the internet at http://www.regulations.gov by searching for and 
locating Docket No. FAA-2018-0380.

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-
0380; 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

    A recent event involving an engine failure due to a fractured fan 
blade resulted in the engine inlet cowl disintegrating and debris 
penetrating the fuselage, causing a loss of pressurization, and 
prompting an emergency descent. One passenger fatality occurred as a 
result. In response to this event, the FAA issued Emergency

[[Page 19177]]

AD 2018-09-51 (``AD 2018-09-51''), to address certain high-time CFM56-
7B engines, specifically including those with 30,000 or more total 
accumulated flight cycles since new. AD 2018-09-51 requires a one-time 
ultrasonic inspection (USI) of the concave and convex sides of the fan 
blade dovetail.
    Since the issuance of AD 2018-09-51, the FAA has been working 
closely with CFM to develop an additional compliance plan to address 
the risk of fan blade failure for the entire CFM56-7B fleet. This AD 
addresses the unsafe condition affecting CFM56-7B engines by requiring 
initial and repetitive inspections of fan blades based on accumulated 
fan blade cycles. This condition, if not addressed, could result in fan 
blade failure due to cracking, which could lead to in an engine in-
flight shutdown (IFSD), uncontained release of debris, damage to the 
airplane, and possible airplane decompression. 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) CFM56-7B S/B 72-1033, dated 
April 20, 2018, and Subtask 72-21-01-220-091, of Task 72-21-01-200-001, 
from the CFM56-7B Engine Shop Manual (ESM), Revision 57, dated January 
15, 2018. CFM SB CFM56-7B S/B 72-1033 describes procedures for 
performing a USI of the affected fan blades. Subtask 72-21-01-220-091, 
of Task 72-21-01-200-001, from the CFM56-7B ESM, describes procedures 
for performing an eddy current inspection (ECI) of the affected fan 
blades. This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Other Related Service Information

    We also reviewed CFM SB CFM56-7B S/B 72-1019, dated March 24, 2017, 
and Revision 1, dated June 13, 2017; CFM SB CFM56-7B S/B 72-1024, dated 
July 26, 2017; and General Electric Field Support Technology (FST) 
procedure 2370, dated December 9, 2016. These SBs and the FST procedure 
provide information on performing the USI inspection.

Other Related Rulemaking

    The FAA previously issued a Notice of Proposed Rulemaking (see 
Docket No. FAA-2017-0313 at http://www.regulations.gov), to address an 
unsafe condition based on a similar event that occurred in 2016. We 
will be withdrawing that proposal because this new action represents a 
more comprehensive corrective action plan than previously proposed.

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 initial and repetitive USIs or ECIs of certain fan 
blades and, if they fail the inspection, their replacement with parts 
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 adoption of this rule 
because certain fan blades must be inspected, and, if needed, replaced 
before further flight. Failure to inspect and replace these parts 
within the required compliance times could lead to failure of the fan 
blades, engine IFSD, uncontained release of debris, damage to the 
airplane, and possible airplane decompression. 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-
0380 and Product Identifier 2018-NE-14-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 3,716 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
----------------------------------------------------------------------------------------------------------------
Inspect engine fan blade..............  2 work-hours x $85 per                $0            $170        $631,720
                                         hour = $170.
----------------------------------------------------------------------------------------------------------------

    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 these 
replacements:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                    Action                                 Labor cost               Parts cost        product
----------------------------------------------------------------------------------------------------------------
Replace fan blade.............................  1 work-hour x $85 per hour = $85          $8,500          $8,585
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[[Page 19178]]

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):

2018-09-10 CFM International S.A.: Amendment 39-19267; Docket No. 
FAA-2018-0380; Product Identifier 2018-NE-14-AD.

(a) Effective Date

    This AD is effective May 14, 2018.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to CFM International S.A. (CFM) CFM56-7B20, 
CFM56-7B22, CFM56-7B22/B1, CFM56-7B24, CFM56-7B24/B1, CFM56-7B26, 
CFM56-7B26/B2, CFM56-7B27, CFM56-7B27A, CFM56-7B26/B1, CFM56-7B27/
B1, CFM56-7B27/B3, CFM56-7B20/2, CFM56-7B22/2, CFM56-7B24/2, CFM56-
7B26/2, CFM56-7B27/2, CFM56-7B20/3, CFM56-7B22/3, CFM56-7B22/3B1, 
CFM56-7B24/3, CFM56-7B24/3B1, CFM56-7B26/3, CFM56-7B26/3B1, CFM56-
7B26/3B2, CFM56-7B27/3, CFM56-7B27/3B1, CFM56-7B27/3B3, CFM56-7B27A/
3, CFM56-7B26/3F, CFM56-7B26/3B2F, CFM56-7B27/3F, CFM56-7B27/3B1F, 
CFM56-7B20E, CFM56-7B22E, CFM56-7B22E/B1, CFM56-7B24E, CFM56-7B24E/
B1, CFM56-7B26E, CFM56-7B26E/B1, CFM56-7B26E/B2, CFM56-7B27AE, 
CFM56-7B27E, CFM56-7B27E/B1, CFM56-7B27E/B3, CFM56-7B26E/F, CFM56-
7B26E/B2F, CFM56-7B27E/F, and CFM56-7B27E/B1F engine models.

(d) Subject

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

(e) Unsafe Condition

    This AD was prompted by a recent engine failure due to a fan 
blade fracture that resulted in the engine inlet cowl disintegrating 
and debris penetrating the fuselage, causing a loss of 
pressurization, and prompting an emergency descent. We are issuing 
this AD to prevent failure of the fan blade. The unsafe condition, 
if not addressed, could result in failure of the fan blade, the 
engine inlet cowl disintegrating and debris penetrating the 
fuselage, causing a loss of pressurization, and prompting an 
emergency descent.

(f) Compliance

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

(g) Required Actions

    (1) Perform an ultrasonic inspection (USI) or eddy current 
inspection (ECI) of the concave and convex sides of the fan blade 
dovetail as follows:
    (i) Perform an initial inspection on each fan blade before the 
fan blade accumulates 20,000 cycles since new, or within 113 days 
from the effective date of this AD, whichever occurs later.
    (ii) If cycles since new on a fan blade is unknown, perform an 
initial inspection within 113 days from the effective date of this 
AD.
    (iii) Thereafter, repeat this inspection no later than 3,000 
cycles since the last inspection.
    (iv) Use the Accomplishment Instructions, paragraphs 3.A.(3)(a) 
through (i), of CFM Service Bulletin (SB) CFM56-7B S/B 72-1033, 
dated April 20, 2018, to perform a USI or use the instructions in 
subtask 72-21-01-220-091, of task 72-21-01-200-001, from CFM CFM56-
7B Engine Shop Manual, Revision 57, dated January 15, 2018, to 
perform an ECI.
    (2) If any unserviceable indication, as specified in the 
applicable service information in paragraph (g)(1)(iv) of this AD, 
is found during the inspections required by paragraph (g) of this 
AD, replace the fan blade before further flight with a part eligible 
for installation.

(h) Installation Prohibition

    Do not install any replacement fan blade unless it meets one of 
the following criteria:
    (1) The replacement fan blade has fewer than 20,000 cycles since 
new, or;
    (2) The replacement fan blade has been inspected within the last 
300 cycles in accordance with paragraph (g) of this AD.

(i) Definition

    For the purpose of this AD, a ``replacement fan blade'' is a fan 
blade that is being installed into an engine from which it was not 
previously removed. Removing and reinstalling a fan blade for the 
purpose of relubrication is not subject to the Installation 
Prohibition of this AD.

(j) Credit for Previous Actions

    (1) You may take credit for the USI required by paragraph (g) of 
this AD, if those actions were performed before the effective date 
of this AD using CFM SB CFM56-7B S/B 72-1019, dated March 24, 2017; 
or Revision 1, dated June 13, 2017; or CFM SB CFM56-7B S/B 72-1024, 
dated July 26, 2017; or General Electric Field Support Technology 
procedure 2370, dated December 9, 2016.
    (2) You may take credit for the ECI required by paragraph (g) of 
this AD, if those actions were performed before the effective date 
of this AD using the instructions in subtask 72-21-01-220-091, of 
task 72-21-01-200-001, from CFM56-7B Engine Shop Manual, earlier 
than Revision 57, dated January 15, 2018.

[[Page 19179]]

(k) 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 (l) 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.

(l) 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].

(m) 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 International, S.A. (CFM) Service Bulletin CFM56-7B S/B 
72-1033, dated April 20, 2018.
    (ii) Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from 
the CFM CFM56-7B Engine Shop Manual, Revision 57, dated January 15, 
2018.
    (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 the FAA, Engine and 
Propeller Standards Branch, Policy and Innovation Division, 1200 
District Avenue, Burlington, MA. 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 April 27, 2018.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-09338 Filed 5-1-18; 8:45 am]
BILLING CODE 4910-13-P


