AD 2018-10-11

[Federal Register Volume 83, Number 96 (Thursday, May 17, 2018)]
[Rules and Regulations]
[Pages 22836-22839]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2018-10657]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0443; Product Identifier 2018-NE-14-AD; Amendment 
39-19286; AD 2018-10-11]
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 superseding Airworthiness Directive (AD) 2018-09-10 for 
all CFM International S.A. (CFM) Model CFM56-7B engines. AD 2018-09-10 
required 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 requires the same initial and 
repetitive inspections but revises the compliance time for the initial 
inspections of certain higher-risk fan blades. 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 June 1, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of June 1, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of May 
14, 2018 (83 FR 19176, May 2, 2018).
    We must receive any comments on this AD by July 2, 2018.

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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>. 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: <a href="/cdn-cgi/l/email-protection#ceafb8a7afbaa7a1a0e0a8a2ababbabdbbbebea1bcba8ea9abe0ada1a3"><span class="__cf_email__" data-cfemail="a0c1d6c9c1d4c9cfce8ec6ccc5c5d4d3d5d0d0cfd2d4e0c7c58ec3cfcd">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and 
locating Docket No. FAA-2018-0443.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0443; 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-

[[Page 22837]]

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: <a href="/cdn-cgi/l/email-protection#42212a302b316c2f2125372b3027022423236c252d34"><span class="__cf_email__" data-cfemail="63000b110a104d0e0004160a1106230502024d040c15">[email&#160;protected]</span></a>.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued AD 2018-09-10, Amendment 39-19267 (83 FR 19176, May 2, 
2018), (``AD 2018-09-10''), for all CFM model CFM56-7B engines. AD 
2018-09-10 required 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. AD 2018-09-10 resulted from a 
recent event involving an engine failure due to a fractured fan blade 
leading to 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. We 
issued AD 2018-09-10 to prevent failure of the fan blade due to 
cracking, which could lead to an engine in-flight shutdown (IFSD), 
uncontained release of debris, damage to the airplane, and possible 
airplane decompression.

Actions Since AD 2018-09-10 Was Issued

    Since we issued AD 2018-09-10, an investigation of this event has 
determined new methods for identifying applicable parts as well as the 
need to reduce the compliance time for certain fan blades. Therefore, 
this AD requires inspection of higher risk fan blades, identified using 
one of the methods in CFM Service Bulletin (SB) CFM56-7B S/B 72-1033, 
Revision 01, dated May 9, 2018, within 30 days from the effective date 
of the AD. The remaining fan blades must be inspected within 90 days 
from the effective date of the AD or prior to accumulating 20,000 
flight cycles. We are issuing this AD to address the unsafe condition 
on these products.

Related Service Information Under 1 CFR Part 51

    We reviewed CFM SB CFM56-7B S/B 72-1033, Revision 01, dated May 9, 
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, Revision 01, describes procedures for 
performing an ultrasonic inspection (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 CFM SB CFM56-7B S/B 72-1033, dated April 20, 2018, 
and General Electric Field Support Technology (FST) procedure 2370, 
dated December 9, 2016. These SBs and the FST provide information on 
performing the USI.

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 ultrasonic or eddy current 
inspection 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 we did not provide you with notice and an opportunity to 
provide your comments before it becomes effective. 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-2018-0443 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a>, 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.
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    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:

[[Page 22838]]



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

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 part 39 of the Federal Aviation 
Regulations (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 removing Airworthiness Directive (AD) 
2018-09-10, Amendment 39-19267 (83 FR 19176, May 2, 2018) and adding 
the following new AD:

2018-10-11 CFM International S.A.: Amendment 39-19286; Docket No. 
FAA-2018-0443; Product Identifier 2018-NE-14-AD.

(a) Effective Date

    This AD is effective June 1, 2018.

(b) Affected ADs

    This AD replaces AD 2018-09-10, Amendment 39-19267 (83 FR 19176, 
May 2, 2018).

(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 leading to 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. 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) Within 30 days after the effective date of this AD, perform 
an initial inspection of the fan blades identified using the 
criteria in Planning Information, either paragraph 1.C.2.(a), 
1.C.2.(b), or 1.C.2.(c), of CFM Service Bulletin (SB) CFM56-7B S/B 
72-1033, Revision 01, dated May 9, 2018.
    (ii) For all fan blades not inspected in accordance with 
paragraph (g)(1)(i) of this AD, perform an initial inspection prior 
to accumulating 20,000 flight cycles on the fan blade or within 90 
days from the effective date of this AD, whichever occurs later.
    (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 SB CFM56-7B S/B 72-1033, Revision 01, dated May 
9, 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 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

[[Page 22839]]

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; CFM SB CFM56-7B S/B 72-1033, dated April 20, 2018; or General 
Electric Field Support Technology procedure 2370, dated December 9, 
2016.
    (2) You may take credit for an ECI using the instructions in 
Subtask 72-21-01-220-091, of Task 72-21-01-200-001, from the CFM56-
7B Engine Shop Manual, earlier than Revision 57, dated January 15, 
2018.

(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: <a href="/cdn-cgi/l/email-protection#96d7d8d3bbd7d2bbd7dbd9d5d6f0f7f7b8f1f9e0"><span class="__cf_email__" data-cfemail="8bcac5cea6cacfa6cac6c4c8cbedeaeaa5ece4fd">[email&#160;protected]</span></a>.
    (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.
    (3) For service information that contains steps that are labeled 
as Required for Compliance (RC), the provisions of paragraphs 
(k)(3)(i) and (k)(3)(ii) of this AD apply.
    (i) The steps labeled as RC, including substeps under an RC step 
and any figures identified in an RC step, must be done to comply 
with the AD. An AMOC is required for any deviations to RC steps, 
including substeps and identified figures.
    (ii) Steps not labeled as RC may be deviated from using accepted 
methods in accordance with the operator's maintenance or inspection 
program without obtaining approval of an AMOC, provided the RC 
steps, including substeps and identified figures, can still be done 
as specified, and the airplane can be put back in an airworthy 
condition.

(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: 
<a href="/cdn-cgi/l/email-protection#781b100a110b56151b1f0d110a1d381e1919561f170e"><span class="__cf_email__" data-cfemail="99faf1ebf0eab7f4fafeecf0ebfcd9fff8f8b7fef6ef">[email&#160;protected]</span></a>.

(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.
    (3) The following service information was approved for IBR on 
June 1, 2018.
    (i) CFM Service Bulletin (SB) CFM56-7B S/B 72-1033, Revision 01, 
dated May 9, 2018.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
May 14, 2018 (83 FR 19176, May 2, 2018).
    (i) 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.
    (ii) Reserved.
    (5) 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: <a href="/cdn-cgi/l/email-protection#9afbecf3fbeef3f5f4b4fcf6ffffeee9efeaeaf5e8eedafdffb4f9f5f7"><span class="__cf_email__" data-cfemail="c5a4b3aca4b1acaaabeba3a9a0a0b1b6b0b5b5aab7b185a2a0eba6aaa8">[email&#160;protected]</span></a>.
    (6) 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.
    (7) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Burlington, Massachusetts, on May 15, 2018.
Robert J. Ganley,
Manager, Engine & Propeller Standards Branch, Aircraft Certification 
Service.
[FR Doc. 2018-10657 Filed 5-16-18; 8:45 am]
 BILLING CODE 4910-13-P