Airworthiness Directives; CFM International S.A. Turbofan Engines, 61529-61531 [2018-26026]
Download as PDF
<![CDATA[
Federal Register / Vol. 83, No. 231 / Friday, November 30, 2018 / Rules and Regulations
Issued in Burlington, Massachusetts, on
November 27, 2018.
Robert J. Ganley,
Manager, Engine and Propeller Standards
Branch, Aircraft Certification Service.
[FR Doc. 2018–26038 Filed 11–29–18; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
amozie on DSK3GDR082PROD with RULES
Examining the AD Docket
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:
• 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–
SUMMARY:
VerDate Sep<11>2014
16:03 Nov 29, 2018
Jkt 247001
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–
0869.
You may examine the AD docket on
the internet at https://
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: chris.mcguire@faa.gov.
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 newlymanufactured 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.
PO 00000
Frm 00021
Fmt 4700
Sfmt 4700
61529
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,
E:\FR\FM\30NOR1.SGM
30NOR1
61530
Federal Register / Vol. 83, No. 231 / Friday, November 30, 2018 / Rules and Regulations
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 two
engines installed on airplanes of U.S.
registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Remove HPT case and FPI of forward flange
1000 work-hour × $85 per 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
Cost per
product
Parts cost
$179,400
$264,400
Cost on
U.S. operators
$528,800
determining the number of aircraft that
might need this replacement:
ON-CONDITION COSTS
Action
Labor cost
Replace combustion case assembly ............................
10 work-hours × $85 per hour = $850 .........................
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.
Regulatory Findings
16:03 Nov 29, 2018
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Jkt 247001
§ 39.13
$558,800
Cost per
product
$559,650
[Amended]
2. The FAA amends § 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 highpressure 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.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(d) Subject
PART 39—AIRWORTHINESS
DIRECTIVES
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.
1. The authority citation for part 39
continues to read as follows:
■
This AD will not have federalism
implications under Executive Order
VerDate Sep<11>2014
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.
Parts cost
Authority: 49 U.S.C. 106(g), 40113, 44701.
PO 00000
Frm 00022
Fmt 4700
Sfmt 4700
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
(e) Unsafe Condition
E:\FR\FM\30NOR1.SGM
30NOR1
Federal Register / Vol. 83, No. 231 / Friday, November 30, 2018 / Rules and Regulations
(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.
(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: 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.
(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:
chris.mcguire@faa.gov.
amozie on DSK3GDR082PROD with RULES
(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.
16:03 Nov 29, 2018
Jkt 247001
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]
BILLING CODE 4910–13–P
DEPARTMENT OF HOMELAND
SECURITY
Coast Guard
(h) Alternative Methods of Compliance
(AMOCs)
VerDate Sep<11>2014
(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: aviation.fleetsupport@ge.com.
(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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
33 CFR Part 117
[Docket No. USCG–2018–1035]
Drawbridge Operation Regulation;
Atlantic Intracoastal Waterway,
Albemarle and Chesapeake Canal,
Chesapeake, VA
Coast Guard, DHS.
Notice of deviation from
drawbridge regulation.
AGENCY:
ACTION:
The Coast Guard has issued a
temporary deviation from the operating
schedule that governs the S168/Great
Bridge bridge. This bridge carries SR168
(Battlefield Boulevard South) over the
Atlantic Intracoastal Waterway (AICW),
Albemarle and Chesapeake Canal, mile
12.0, at Chesapeake, VA. The deviation
is necessary to facilitate the Annual
Chesapeake Rotary Christmas Parade.
This deviation allows the bridge to
remain in the closed-to-navigation
position.
SUMMARY:
The deviation is effective from 4
p.m. to 10 p.m., on Saturday, December
1, 2018.
ADDRESSES: The docket for this
deviation, USCG–2018–1035 is available
at https://www.regulations.gov. Type the
docket number in the ‘‘SEARCH’’ box
DATES:
PO 00000
Frm 00023
Fmt 4700
Sfmt 4700
61531
and click ‘‘SEARCH’’. Click on Open
Docket Folder on the line associated
with this deviation.
FOR FURTHER INFORMATION CONTACT: If
you have questions on this temporary
deviation, call or email Mr. Michael
Thorogood, Bridge Administration
Branch Fifth District, Coast Guard,
telephone 757–398–6557, email
Michael.R.Thorogood@uscg.mil.
SUPPLEMENTARY INFORMATION: The City
of Chesapeake owner and operator of
the S168/Great Bridge bridge has
requested a temporary deviation from
the current operating regulations to
ensure the safety of the increased
volumes of spectators that will be
participating in the Annual Chesapeake
Rotary Christmas Parade on Saturday,
December 1, 2018. The S168/Great
Bridge Bridge carries SR 168/Battlefield
Boulevard South over the Atlantic
Intracoastal Waterway (AICW),
Albemarle and Chesapeake Canal, mile
12.0, at Chesapeake, VA. This bridge is
a double bascule drawbridge and has a
vertical clearance of 8 feet above mean
high water in the closed position. The
bridge has an unlimited vertical
clearance in the open position.
The current operating regulation is set
out in 33 CFR 117.997(g). Under this
temporary deviation, the bridge will be
maintained in the closed-to-navigation
position from 4 p.m. to 6 p.m. and from
8 p.m. to 10 p.m. on Saturday,
December 1, 2018.
The AICW, Albemarle and
Chesapeake Canal, is used by a variety
of vessels including U.S. government
vessels, small commercial vessels,
recreational vessels and tug and barge
traffic. The Coast Guard has carefully
considered the nature and volume of
vessel traffic on the waterway in
publishing this temporary deviation.
Vessels able to pass through the
bridge in the closed-to-navigation
position may do so at any time. The
bridge will be able to open for
emergencies and there is no immediate
alternative route for vessels unable to
pass through the bridge in the closed
position. The Coast Guard will also
inform the users of the waterway
through our Local and Broadcast
Notices to Mariners of the change in
operating schedule for the bridge so that
vessel operators can arrange their
transits to minimize any impact caused
by the temporary deviation.
In accordance with 33 CFR 117.35(e),
the drawbridge must return to its regular
operating schedule immediately at the
end of the effective period of this
temporary deviation. This deviation
from the operating regulations is
authorized under 33 CFR 117.35.
E:\FR\FM\30NOR1.SGM
30NOR1
]]>Agencies
[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]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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:
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-2018-0869.
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-
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 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 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: https://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]
BILLING CODE 4910-13-P
