Airworthiness Directives; Airbus SAS Airplanes, 28719-28722 [2019-13059]
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Federal Register / Vol. 84, No. 119 / Thursday, June 20, 2019 / Rules and Regulations
(B) that has been removed from the original
HPT disk and re-assembled to a different
HPT disk; and
(C) that has 3,751 or more cycles since
being reconfigured.
(ii) [Reserved]
(d) Subject
Joint Aircraft System Component (JASC)
Code 7250, Turbine Section.
(e) Unsafe Condition
This AD was prompted by cracks found in
the rotating air HPT front seal. The FAA is
issuing this AD to prevent failure of the
rotating air HPT front seal. The unsafe
condition, if not addressed, could result in
the uncontained release of the rotating air
HPT front seal, damage to the engine, and
damage to the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Required Actions
(1) For all affected CFM CFM56–5B and
CFM56–7B model turbofan engines:
(i) If, on the effective date of this AD, the
rotating air HPT front seal has 7,000 cycles
or greater since being reconfigured, remove
the part from service within 50 cycles after
the effective date of this AD and replace with
a part eligible for installation.
(ii) If, on the effective date of this AD, the
rotating air HPT front seal has between 6,001
and 6,999 cycles, inclusive, since being
reconfigured, remove the part from service
within 500 cycles after the effective date of
this AD, but not to exceed 7,050 cycles since
being reconfigured, and replace with a part
eligible for installation.
(2) For all affected CFM CFM56–5C model
turbofan engines:
(i) If, on the effective date of this AD, the
rotating air HPT front seal has 4,250 cycles
or greater since being reconfigured, remove
the part from service within 25 cycles after
the effective date of this AD, or within 1,500
cycles since the last fluorescent penetrant
inspection (FPI) of the rotating air HPT front
seal, whichever occurs later, and replace
with a part eligible for installation.
(ii) If, on the effective date of this AD, the
rotating air HPT front seal has between 3,751
and 4,249 cycles, inclusive, since being
reconfigured, remove the part from service
within 250 cycles after the effective date of
this AD, before accumulating 4,275 cycles
since being reconfigured, or within 1,500
cycles since the last FPI of the rotating air
HPT front seal, whichever occurs later, and
replace with a part eligible for installation.
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(h) Definition
For the purpose of this AD, reconfigured is
when a rotating air HPT front seal has been
removed from the original HPT disk and reassembled to a different HPT disk.
(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,
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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.
Issued in Burlington, Massachusetts, on
June 14, 2019.
Karen M. Grant,
Acting Manager, Engine and Propeller
Standards Branch, Aircraft Certification
Service.
[FR Doc. 2019–13040 Filed 6–19–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–1068; Product
Identifier 2018–NM–140–AD; Amendment
39–19655; AD 2019–11–09]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
The FAA is adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A319–113 and –114
airplanes, and Model A320–211 and
–212 airplanes. This AD was prompted
by a report that a life-limit of 64,000
flight cycles has been established for
certain titanium crossbeams of the
forward engine mount. This AD requires
repetitive replacements of all affected
crossbeams of the forward engine
mount, as specified in European
Aviation Safety Agency (EASA) ADs,
which are incorporated by reference.
The FAA is issuing this AD to address
the unsafe condition on these products.
DATES: This AD is effective July 25,
2019.
SUMMARY:
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28719
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of July 25, 2019.
ADDRESSES: For the material
incorporated by reference (IBR) in this
final rule, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990
1000; email ADs@easa.europa.eu;
internet www.easa.europa.eu. You may
find this IBR material on the EASA
website at https://ad.easa.europa.eu.
You may view this IBR material at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available in the AD docket on
the internet at https://
www.regulations.gov.
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–
1068; 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 address for Docket
Operations is U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus SAS Model A319–
113 and –114 airplanes, and Model
A320–211 and –212 airplanes. The
NPRM published in the Federal
Register on February 7, 2019 (84 FR
2465). The NPRM was prompted by a
report that a life-limit of 64,000 flight
cycles has been established for certain
titanium crossbeams of the forward
engine mount. The NPRM proposed to
require repetitive replacements of all
affected crossbeams of the forward
engine mount.
The FAA is issuing this AD to address
failure of a crossbeam of the forward
engine mount, which could result in
detachment of the engine and
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Federal Register / Vol. 84, No. 119 / Thursday, June 20, 2019 / Rules and Regulations
consequent reduced controllability of
the airplane.
The EASA, which is the Technical
Agent for the Member States of the
European Union, has issued EASA AD
2018–0212R1, dated March 28, 2019
(‘‘EASA AD 2018–0212R1’’) (also
referred to as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
for all Airbus SAS Model A319–113 and
–114 airplanes, and Model A320–211
and –212 airplanes. The MCAI states:
The forward engine mount crossbeam of
the CFM56–5A engine, [part number] P/N
238–0204–501, is made of titanium. A life
limit of 64,000 FC [flight cycles] has been
demonstrated. Due to potential transferability
of a crossbeam from one aeroplane to
another, it is necessary to track the life of this
part and to remove it before exceeding the
life limit.
This condition, if not corrected, could lead
to forward engine mount crossbeam failure,
possibly resulting in engine detachment in
flight and consequent reduced control of the
aeroplane.
To address this potential unsafe condition,
Airbus published the SB [Service Bulletin
A320–71–1073, dated June 8, 2018],
providing instructions to identify the P/N of
the crossbeam installed on an aeroplane and
to remove affected crossbeam before
exceeding the life limit. Airbus also issued
SB A320–71–1076, providing modification
instructions for installation of improved
forward engine mount steel crossbeams P/N
642–2002–503. Consequently, EASA issued
AD 2018–0212 [which was referred to as the
appropriate source of service information for
accomplishing the actions specified in the
FAA NPRM], requiring the implementation
of the new life limit for the affected
crossbeams.
Since that [EASA] AD was issued,
following a re-assessment of comments
received during the consultation period of
[Proposed Airworthiness Directive] PAD 18–
091 which preceded EASA AD 2018–0212,
EASA agrees that an affected crossbeam
having P/N 238–0204–501 can be
(re)installed on any aeroplane, provided its
accumulated life is less than the applicable
life limit.
For the reason described above, this
[EASA] AD is revised accordingly.
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You may examine the MCAI in the
AD docket on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
1068.
Support for the NPRM
Donovan Twiddle, Jr., agreed that the
proposed AD should be implemented.
16:16 Jun 19, 2019
Jkt 247001
Delta Air Lines (DAL) asked that the
proposed AD include an exception to
the language in paragraph (2) of EASA
AD 2018–2012, which specifies
‘‘Replacing on an aeroplane any affected
crossbeam with crossbeam having P/N
642–2002–503 in accordance with
instructions provided by Airbus is an
acceptable alternative method to comply
with the requirements of paragraph (1)
of this [EASA] AD, provided that,
following modification, no affected
crossbeam is installed on that
aeroplane.’’ DAL stated that omitting the
language ‘‘provided that, following
modification, no affected crossbeam is
installed on that aeroplane’’ would
allow for the crossbeam having P/N
642–2002–503 to be managed like any
other CFM56 life-limited engine
component, while continuing to
prohibit installing a crossbeam that has
been modified to have P/N 642–2002–
503.
DAL pointed out that, since the
NPRM was published, the EASA has
issued EASA AD 2018–0212R1, which
addresses its original request (described
previously) and, therefore, requested
that the NPRM be revised to refer to
EASA AD 2018–0212R1 as the
appropriate source of information for
complying with the proposed AD.
The FAA agrees that this final rule
should refer to EASA AD 2018–0212R1
for accomplishing the required actions.
As noted by the commenter, paragraph
(2) of EASA AD 2018–0212R1 does not
contain the language ‘‘provided that,
following modification, no affected
crossbeam is installed on that
aeroplane.’’ The agency determined that
no additional work is required for
airplanes that have accomplished the
actions as required by EASA AD 2018–
0212, dated September 28, 2018 (‘‘EASA
AD 2018–0212’’). Therefore, the agency
has revised all applicable sections in
this final rule to also specify EASA AD
2018–0212R1.
Request To Revise Crossbeam
Accumulated Life Definition
Comments
The FAA gave the public the
opportunity to participate in developing
this final rule. The following presents
the comments received on the NPRM
and the FAA’s response to each
comment.
VerDate Sep<11>2014
Request for Exception to EASA AD
Requirement
DAL asked that the FAA revise the
proposed AD to include a revised
definition of crossbeam accumulated
life. DAL stated that it received
information from Airbus indicating that
the data contained in the life estimation
tables of EASA AD 2018–0212 and
EASA AD 2018–0212R1, and in Airbus
Service Bulletin A320–71–1073, dated
June 8, 2018, and Revision 01, dated
January 3, 2019, was generated using
2015 fleet utilization data. DAL noted
that Airbus has received updated fleet
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utilization data from 2017 that better
estimates the flight cycle count for
operators, and substantiates a
compliance window later than the
January 31, 2019 date required by EASA
AD 2018–0212 and EASA AD 2018–
0212R1, and the referenced service
information. DAL added that there are
operators that have the ability to trace
the actual accumulated mount assembly
and crossbeam flight cycles from dates
earlier than ‘‘Life estimation done on’’
date of the life estimation tables
included in Appendix 01 of EASA AD
2018–0212 and EASA AD 2018–0212R1.
DAL explained that Airbus has been
able to provide operators with an
accumulated life estimation that takes
Airbus’s updated fleet utilization Monte
Carlo counting method and the
operator’s actual flight cycle data into
account. DAL went on to explain that
the updated Monte Carlo counting
method also includes crossbeams where
the date of manufacture was not
explicitly known and was assumed to be
before January 1, 1988. For crossbeams
where the date of manufacture was not
identified, DAL stated that it believes
the use of Airbus data and maintenance
records, while still assuming a date of
manufacture before January 1, 1988,
would not adversely affect the level of
safety of the airplane. By still assuming
the worst case scenario for the date of
manufacture, DAL asserted that the
most conservative estimate for
crossbeam accumulated life is still being
used. DAL provided a revised definition
of crossbeam accumulated life, and
stated that the proposed definition
would allow operators to use the
updated Monte Carlo counting method
from Airbus and maintenance records
for all crossbeams, as well as also taking
into account the fact that the final rule
should require the use of ‘‘total flight
cycles.’’
The FAA does not agree with the
commenter’s request. The agency has
not received any new life estimation
data either from EASA or Airbus, other
than that referenced in EASA AD 2018–
0212R1. After the NPRM comment
period closed, the FAA contacted
EASA; EASA confirmed that the life
estimation table in Appendix 1 of EASA
AD 2018–0212R1 is based on the latest
data received from Airbus. In addition,
the agency does not have access to the
latest data referenced by DAL. In order
to calculate flight cycles based on new
fleet utilization information received
from Airbus, which would allow DAL to
continue operation with the affected
part later than EASA’s estimation, DAL
may request approval of an alternative
method of compliance (AMOC) under
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Federal Register / Vol. 84, No. 119 / Thursday, June 20, 2019 / Rules and Regulations
the provisions of paragraph (i)(1) of this
AD. The FAA has not changed this AD
regarding this issue.
Conclusion
The FAA reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
The FAA has determined that these
minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
The FAA has also determined that
these changes will not increase the
economic burden on any operator or
increase the scope of this final rule.
Related IBR Material Under 1 CFR Part
51
EASA ADs 2018–0212 and 2018–
0212R1 describe procedures for
repetitive replacements of all affected
crossbeams of the forward engine mount
and an optional replacement as an
acceptable method of compliance for the
28721
required replacement. These documents
are distinct since AD 2018–0212R1
includes updated requirements and
definitions, and references updated
service information. This material 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.
Costs of Compliance
The FAA estimates that this AD
affects 59 airplanes of U.S. registry. The
FAA estimates the following costs to
comply with this AD:
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ESTIMATED COSTS FOR REQUIRED ACTIONS
Labor cost
Parts cost
Cost per
product
Up to 134 work-hours × $85 per hour = Up
to $11,390.
Up to $23,278 ..........................
Up to $34,668 ..........................
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.
The FAA is 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 transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
Regulatory Findings
This AD will not have federalism
implications under Executive Order
13132. This AD will not have a
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16:16 Jun 19, 2019
Jkt 247001
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) Will not affect intrastate aviation
in Alaska, and
(3) 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.
Cost on U.S.
operators
Up to $2,045,412.
(a) Effective Date
This AD is effective July 25, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model
A319–113 and –114 airplanes, and Model
A320–211 and –212 airplanes, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of
America Code 71, Powerplant.
Adoption of the Amendment
(e) Reason
This AD was prompted by a report that a
life-limit of 64,000 flight cycles has been
established for certain titanium crossbeams
of the forward engine mount. The FAA is
issuing this AD to address failure of a
crossbeam of the forward engine mount,
which could result in detachment of the
engine and consequent reduced
controllability of the airplane.
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
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):
■
2019–11–09 Airbus SAS: Amendment 39–
19655; Docket No. FAA–2018–1068;
Product Identifier 2018–NM–140–AD.
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(g) Requirements
Except as specified in paragraph (h) of this
AD: Comply with all required actions and
compliance times specified in, and in
accordance with European Aviation Safety
Agency (EASA) AD 2018–0212, dated
September 28, 2018 (‘‘EASA AD 2018–
0212’’), or EASA AD 2018–0212R1, dated
March 28, 2019 (‘‘EASA AD 2018–0212R1’’).
(h) Exceptions to EASA ADs 2018–0212 and
2018–0212R1
(1) For purposes of determining
compliance with the requirements of this AD:
Where EASA ADs 2018–0212 and 2018–
0212R1 refer to the effective date of EASA
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Federal Register / Vol. 84, No. 119 / Thursday, June 20, 2019 / Rules and Regulations
AD 2018–0212 (October 12, 2018), this AD
requires using the effective date of this AD.
(2) Where paragraph (2) of EASA ADs
2018–0212 and 2018–0212R1 specifies
replacing ‘‘with instructions provided by
Airbus,’’ for this AD, the replacement must
be done using a method approved in
accordance with the procedures specified in
paragraph (i)(2) of this AD.
(3) Where paragraphs (1) and (3) of EASA
ADs 2018–0212 and 2018–0212R1 specify
flight cycles (FC), this AD requires using
‘‘total flight cycles.’’
(4) The ‘‘Remarks’’ sections of EASA ADs
2018–0212 and 2018–0212R1 do not apply.
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(i) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards 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 International Section, send it
to the attention of the person identified in
paragraph (j) of this AD. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@
faa.gov. 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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain instructions
from a manufacturer, the instructions must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or EASA;
or Airbus SAS’s EASA Design Organization
Approval (DOA). If approved by the DOA,
the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): For any
service information referenced in EASA AD
2018–0212 or EASA AD 2018–0212R1 that
contains RC procedures and tests: Except as
required by paragraph (i)(2) of this AD, RC
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
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 procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(j) Related Information
For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(k) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
VerDate Sep<11>2014
16:16 Jun 19, 2019
Jkt 247001
(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 this AD specifies otherwise.
(i) European Aviation Safety Agency
(EASA) AD 2018–0212, dated September 28,
2018.
(ii) European Aviation Safety Agency
(EASA) AD 2018–0212R1, dated March 28,
2019.
(3) For EASA AD 2018–0212 and EASA AD
2018–0212R1, contact the EASA, KonradAdenauer-Ufer 3, 50668 Cologne, Germany;
telephone +49 221 89990 6017; email ADs@
easa.europa.eu; internet
www.easa.europa.eu. You may find these
EASA ADs on the EASA website at https://
ad.easa.europa.eu.
(4) You may view these EASA ADs at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
EASA AD 2018–0212 and EASA AD 2018–
0212R1 may be found in the AD docket on
the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2018–1068.
(5) You may view this material 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/federalregister/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on June
10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–13059 Filed 6–19–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2019–0407; Product
Identifier 2019–NM–075–AD; Amendment
39–19648; AD 2019–11–02]
Examining the AD Docket
RIN 2120–AA64
Airworthiness Directives; The Boeing
Company Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
The FAA is superseding
Airworthiness Directive (AD) 2017–16–
10, which applied to all The Boeing
Company Model 777 airplanes. AD
2017–16–10 required repetitive
inspections of the left and right side
underwing longerons for any crack, and
related investigative and corrective
SUMMARY:
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actions if necessary. This AD retains the
requirements of AD 2017–16–10,
reduces certain compliance times for
certain airplanes, and removes airplanes
from the applicability. This AD was
prompted by reports of cracks on the
underwing longerons. The FAA is
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective July 5, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of July 5, 2019.
The FAA must receive any comments
on this AD by August 5, 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: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this final rule, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS),
2600 Westminster Blvd., MC 110–SK57,
Seal Beach, CA 90740–5600; phone:
562–797–1717; internet: https://
www.myboeingfleet.com. You may view
this service information at the FAA,
Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2019–
0407.
Sfmt 4700
You may examine the AD docket on
the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2019–
0407; 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 is listed above.
Comments will be available in the AD
docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Eric
Lin, Aerospace Engineer, Airframe
E:\FR\FM\20JNR1.SGM
20JNR1
]]>Agencies
[Federal Register Volume 84, Number 119 (Thursday, June 20, 2019)]
[Rules and Regulations]
[Pages 28719-28722]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-13059]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-1068; Product Identifier 2018-NM-140-AD; Amendment
39-19655; AD 2019-11-09]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: The FAA is adopting a new airworthiness directive (AD) for all
Airbus SAS Model A319-113 and -114 airplanes, and Model A320-211 and -
212 airplanes. This AD was prompted by a report that a life-limit of
64,000 flight cycles has been established for certain titanium
crossbeams of the forward engine mount. This AD requires repetitive
replacements of all affected crossbeams of the forward engine mount, as
specified in European Aviation Safety Agency (EASA) ADs, which are
incorporated by reference. The FAA is issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective July 25, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of July 25,
2019.
ADDRESSES: For the material incorporated by reference (IBR) in this
final rule, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne,
Germany; telephone +49 221 89990 1000; email [email protected];
internet www.easa.europa.eu. You may find this IBR material on the EASA
website at https://ad.easa.europa.eu. You may view this IBR material at
the FAA, Transport Standards Branch, 2200 South 216th St., Des Moines,
WA. For information on the availability of this material at the FAA,
call 206-231-3195. It is also available in the AD docket on the
internet at https://www.regulations.gov.
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-
1068; 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 address for Docket Operations is U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
The FAA issued a notice of proposed rulemaking (NPRM) to amend 14
CFR part 39 by adding an AD that would apply to all Airbus SAS Model
A319-113 and -114 airplanes, and Model A320-211 and -212 airplanes. The
NPRM published in the Federal Register on February 7, 2019 (84 FR
2465). The NPRM was prompted by a report that a life-limit of 64,000
flight cycles has been established for certain titanium crossbeams of
the forward engine mount. The NPRM proposed to require repetitive
replacements of all affected crossbeams of the forward engine mount.
The FAA is issuing this AD to address failure of a crossbeam of the
forward engine mount, which could result in detachment of the engine
and
[[Page 28720]]
consequent reduced controllability of the airplane.
The EASA, which is the Technical Agent for the Member States of the
European Union, has issued EASA AD 2018-0212R1, dated March 28, 2019
(``EASA AD 2018-0212R1'') (also referred to as the Mandatory Continuing
Airworthiness Information, or ``the MCAI''), to correct an unsafe
condition for all Airbus SAS Model A319-113 and -114 airplanes, and
Model A320-211 and -212 airplanes. The MCAI states:
The forward engine mount crossbeam of the CFM56-5A engine, [part
number] P/N 238-0204-501, is made of titanium. A life limit of
64,000 FC [flight cycles] has been demonstrated. Due to potential
transferability of a crossbeam from one aeroplane to another, it is
necessary to track the life of this part and to remove it before
exceeding the life limit.
This condition, if not corrected, could lead to forward engine
mount crossbeam failure, possibly resulting in engine detachment in
flight and consequent reduced control of the aeroplane.
To address this potential unsafe condition, Airbus published the
SB [Service Bulletin A320-71-1073, dated June 8, 2018], providing
instructions to identify the P/N of the crossbeam installed on an
aeroplane and to remove affected crossbeam before exceeding the life
limit. Airbus also issued SB A320-71-1076, providing modification
instructions for installation of improved forward engine mount steel
crossbeams P/N 642-2002-503. Consequently, EASA issued AD 2018-0212
[which was referred to as the appropriate source of service
information for accomplishing the actions specified in the FAA
NPRM], requiring the implementation of the new life limit for the
affected crossbeams.
Since that [EASA] AD was issued, following a re-assessment of
comments received during the consultation period of [Proposed
Airworthiness Directive] PAD 18-091 which preceded EASA AD 2018-
0212, EASA agrees that an affected crossbeam having P/N 238-0204-501
can be (re)installed on any aeroplane, provided its accumulated life
is less than the applicable life limit.
For the reason described above, this [EASA] AD is revised
accordingly.
You may examine the MCAI in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2018-
1068.
Comments
The FAA gave the public the opportunity to participate in
developing this final rule. The following presents the comments
received on the NPRM and the FAA's response to each comment.
Support for the NPRM
Donovan Twiddle, Jr., agreed that the proposed AD should be
implemented.
Request for Exception to EASA AD Requirement
Delta Air Lines (DAL) asked that the proposed AD include an
exception to the language in paragraph (2) of EASA AD 2018-2012, which
specifies ``Replacing on an aeroplane any affected crossbeam with
crossbeam having P/N 642-2002-503 in accordance with instructions
provided by Airbus is an acceptable alternative method to comply with
the requirements of paragraph (1) of this [EASA] AD, provided that,
following modification, no affected crossbeam is installed on that
aeroplane.'' DAL stated that omitting the language ``provided that,
following modification, no affected crossbeam is installed on that
aeroplane'' would allow for the crossbeam having P/N 642-2002-503 to be
managed like any other CFM56 life-limited engine component, while
continuing to prohibit installing a crossbeam that has been modified to
have P/N 642-2002-503.
DAL pointed out that, since the NPRM was published, the EASA has
issued EASA AD 2018-0212R1, which addresses its original request
(described previously) and, therefore, requested that the NPRM be
revised to refer to EASA AD 2018-0212R1 as the appropriate source of
information for complying with the proposed AD.
The FAA agrees that this final rule should refer to EASA AD 2018-
0212R1 for accomplishing the required actions. As noted by the
commenter, paragraph (2) of EASA AD 2018-0212R1 does not contain the
language ``provided that, following modification, no affected crossbeam
is installed on that aeroplane.'' The agency determined that no
additional work is required for airplanes that have accomplished the
actions as required by EASA AD 2018-0212, dated September 28, 2018
(``EASA AD 2018-0212''). Therefore, the agency has revised all
applicable sections in this final rule to also specify EASA AD 2018-
0212R1.
Request To Revise Crossbeam Accumulated Life Definition
DAL asked that the FAA revise the proposed AD to include a revised
definition of crossbeam accumulated life. DAL stated that it received
information from Airbus indicating that the data contained in the life
estimation tables of EASA AD 2018-0212 and EASA AD 2018-0212R1, and in
Airbus Service Bulletin A320-71-1073, dated June 8, 2018, and Revision
01, dated January 3, 2019, was generated using 2015 fleet utilization
data. DAL noted that Airbus has received updated fleet utilization data
from 2017 that better estimates the flight cycle count for operators,
and substantiates a compliance window later than the January 31, 2019
date required by EASA AD 2018-0212 and EASA AD 2018-0212R1, and the
referenced service information. DAL added that there are operators that
have the ability to trace the actual accumulated mount assembly and
crossbeam flight cycles from dates earlier than ``Life estimation done
on'' date of the life estimation tables included in Appendix 01 of EASA
AD 2018-0212 and EASA AD 2018-0212R1. DAL explained that Airbus has
been able to provide operators with an accumulated life estimation that
takes Airbus's updated fleet utilization Monte Carlo counting method
and the operator's actual flight cycle data into account. DAL went on
to explain that the updated Monte Carlo counting method also includes
crossbeams where the date of manufacture was not explicitly known and
was assumed to be before January 1, 1988. For crossbeams where the date
of manufacture was not identified, DAL stated that it believes the use
of Airbus data and maintenance records, while still assuming a date of
manufacture before January 1, 1988, would not adversely affect the
level of safety of the airplane. By still assuming the worst case
scenario for the date of manufacture, DAL asserted that the most
conservative estimate for crossbeam accumulated life is still being
used. DAL provided a revised definition of crossbeam accumulated life,
and stated that the proposed definition would allow operators to use
the updated Monte Carlo counting method from Airbus and maintenance
records for all crossbeams, as well as also taking into account the
fact that the final rule should require the use of ``total flight
cycles.''
The FAA does not agree with the commenter's request. The agency has
not received any new life estimation data either from EASA or Airbus,
other than that referenced in EASA AD 2018-0212R1. After the NPRM
comment period closed, the FAA contacted EASA; EASA confirmed that the
life estimation table in Appendix 1 of EASA AD 2018-0212R1 is based on
the latest data received from Airbus. In addition, the agency does not
have access to the latest data referenced by DAL. In order to calculate
flight cycles based on new fleet utilization information received from
Airbus, which would allow DAL to continue operation with the affected
part later than EASA's estimation, DAL may request approval of an
alternative method of compliance (AMOC) under
[[Page 28721]]
the provisions of paragraph (i)(1) of this AD. The FAA has not changed
this AD regarding this issue.
Conclusion
The FAA reviewed the relevant data, considered the comments
received, and determined that air safety and the public interest
require adopting this final rule with the changes described previously
and minor editorial changes. The FAA has determined that these minor
changes:
Are consistent with the intent that was proposed in the
NPRM for addressing the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
The FAA has also determined that these changes will not increase
the economic burden on any operator or increase the scope of this final
rule.
Related IBR Material Under 1 CFR Part 51
EASA ADs 2018-0212 and 2018-0212R1 describe procedures for
repetitive replacements of all affected crossbeams of the forward
engine mount and an optional replacement as an acceptable method of
compliance for the required replacement. These documents are distinct
since AD 2018-0212R1 includes updated requirements and definitions, and
references updated service information. This material 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.
Costs of Compliance
The FAA estimates that this AD affects 59 airplanes of U.S.
registry. The FAA estimates the following costs to comply with this AD:
Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Up to 134 work-hours x $85 per hour = Up to $23,278.......... Up to $34,668.......... Up to $2,045,412.
Up to $11,390.
----------------------------------------------------------------------------------------------------------------
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.
The FAA is 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 transport category airplanes and
associated appliances to the Director of the System Oversight 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) Will not affect intrastate aviation in Alaska, and
(3) 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):
2019-11-09 Airbus SAS: Amendment 39-19655; Docket No. FAA-2018-1068;
Product Identifier 2018-NM-140-AD.
(a) Effective Date
This AD is effective July 25, 2019.
(b) Affected ADs
None.
(c) Applicability
This AD applies to all Airbus SAS Model A319-113 and -114
airplanes, and Model A320-211 and -212 airplanes, certificated in
any category.
(d) Subject
Air Transport Association (ATA) of America Code 71, Powerplant.
(e) Reason
This AD was prompted by a report that a life-limit of 64,000
flight cycles has been established for certain titanium crossbeams
of the forward engine mount. The FAA is issuing this AD to address
failure of a crossbeam of the forward engine mount, which could
result in detachment of the engine and consequent reduced
controllability of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Requirements
Except as specified in paragraph (h) of this AD: Comply with all
required actions and compliance times specified in, and in
accordance with European Aviation Safety Agency (EASA) AD 2018-0212,
dated September 28, 2018 (``EASA AD 2018-0212''), or EASA AD 2018-
0212R1, dated March 28, 2019 (``EASA AD 2018-0212R1'').
(h) Exceptions to EASA ADs 2018-0212 and 2018-0212R1
(1) For purposes of determining compliance with the requirements
of this AD: Where EASA ADs 2018-0212 and 2018-0212R1 refer to the
effective date of EASA
[[Page 28722]]
AD 2018-0212 (October 12, 2018), this AD requires using the
effective date of this AD.
(2) Where paragraph (2) of EASA ADs 2018-0212 and 2018-0212R1
specifies replacing ``with instructions provided by Airbus,'' for
this AD, the replacement must be done using a method approved in
accordance with the procedures specified in paragraph (i)(2) of this
AD.
(3) Where paragraphs (1) and (3) of EASA ADs 2018-0212 and 2018-
0212R1 specify flight cycles (FC), this AD requires using ``total
flight cycles.''
(4) The ``Remarks'' sections of EASA ADs 2018-0212 and 2018-
0212R1 do not apply.
(i) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards 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 International Section, send it to the attention of
the person identified in paragraph (j) of this AD. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS[email protected]. 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain instructions from a manufacturer, the instructions must be
accomplished using a method approved by the Manager, International
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's
EASA Design Organization Approval (DOA). If approved by the DOA, the
approval must include the DOA-authorized signature.
(3) Required for Compliance (RC): For any service information
referenced in EASA AD 2018-0212 or EASA AD 2018-0212R1 that contains
RC procedures and tests: Except as required by paragraph (i)(2) of
this AD, RC procedures and tests must be done to comply with this
AD; any procedures or tests that are not identified as RC are
recommended. Those procedures and tests that are not identified 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 procedures and tests identified as
RC can be done and the airplane can be put back in an airworthy
condition. Any substitutions or changes to procedures or tests
identified as RC require approval of an AMOC.
(j) Related Information
For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(k) 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 this AD specifies otherwise.
(i) European Aviation Safety Agency (EASA) AD 2018-0212, dated
September 28, 2018.
(ii) European Aviation Safety Agency (EASA) AD 2018-0212R1,
dated March 28, 2019.
(3) For EASA AD 2018-0212 and EASA AD 2018-0212R1, contact the
EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49
221 89990 6017; email [email protected]; internet
www.easa.europa.eu. You may find these EASA ADs on the EASA website
at https://ad.easa.europa.eu.
(4) You may view these EASA ADs at the FAA, Transport Standards
Branch, 2200 South 216th St., Des Moines, WA. For information on the
availability of this material at the FAA, call 206-231-3195. EASA AD
2018-0212 and EASA AD 2018-0212R1 may be found in the AD docket on
the internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2018-1068.
(5) You may view this material 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 Des Moines, Washington, on June 10, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-13059 Filed 6-19-19; 8:45 am]
BILLING CODE 4910-13-P
