[Federal Register Volume 84, Number 76 (Friday, April 19, 2019)]
[Rules and Regulations]
[Pages 16386-16390]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-07940]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0903; Product Identifier 2018-NM-113-AD; Amendment
39-19616; AD 2019-07-05]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-19-14,
which applied to certain Airbus SAS Model A318 and A319 series
airplanes; Model A320-211, -212, -214, -231, -232, and -233 airplanes;
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. AD 2016-19-14 required repetitive inspections for cracking
of the 10VU rack fitting lugs, and repair of any cracking. Since we
issued AD 2016-19-14, we have determined that the unsafe condition may
exist on additional airplanes. This AD continues to require repetitive
inspections for cracking of the 10VU rack fitting lugs, and repair of
any cracking. This AD also adds airplanes to the applicability. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective May 24, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of May 24, 2019.
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email [email protected];
internet http://www.airbus.com. You may view this referenced 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 http://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0903.
Examining the AD Docket
You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0903; 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 (phone: 800-647-
5527) 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
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-19-14, Amendment 39-18663 (81 FR 71602,
October 18, 2016) (``AD 2016-19-14''). AD 2016-19-14 applied to certain
Airbus SAS Model A318 and A319 series airplanes; Model A320-211, -212,
-214, -231, -232, and -233 airplanes; and Model A321-111, -112, -131, -
211, -212, -213, -231, and -232 airplanes. The NPRM published in the
Federal Register on November 5, 2018 (83 FR 55299). Since we issued AD
2016-19-14, we have determined that the unsafe condition may exist on
additional airplanes. This AD continues to require repetitive
inspections for cracking of the 10VU rack fitting lugs, and repair of
any cracking. This AD also adds airplanes to the applicability. We are
issuing this AD to address reading difficulties of flight-critical
information displayed to the flightcrew during a critical phase of
flight, such as an approach or takeoff, which could result in loss of
airplane
[[Page 16387]]
control at an altitude insufficient for recovery.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0131, dated June 19, 2018 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition for all Airbus SAS Model A318 and A319 series
airplanes; Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes; and Model A321-111, -112, -131, -211, -212, -213, -231, and
-232 airplanes. The MCAI states:
During an unscheduled maintenance operation on an A330
aeroplane, the 10VU rack was removed for access and cracks were
discovered on 10VU rack side fittings on lugs 1, 3 and 4. As a
similar design is installed on A320 family aeroplanes, a sampling
review was done to determine the possible fleet impact. The result
showed that several aeroplanes had cracked or broken 10VU rack side
fittings.
This condition, if not detected and corrected, could lead to a
high vibration level on the primary flight and navigation displays
during critical flight phases (take-off and landing), possibly
creating reading difficulties for the crew.
Prompted by these findings, Airbus developed mod 35869 to
reinforce the affected rack fitting lugs. For in-service aeroplanes,
Airbus published SB [service bulletin] A320-92-1087 to provide
detailed inspection (DET) and repair instructions. Consequently,
EASA AD 2015-0170 [which corresponds to FAA AD 2016-19-14] was
issued to require, for all pre mod 35869 aeroplanes, repetitive DET
of the affected 10VU rack fitting lugs and, depending on findings,
accomplishment of a repair.
Since that [EASA] AD was issued, analysis confirmed the need to
extend the inspection to post mod 35869 aeroplanes. Airbus issued SB
A320-92-1119 providing instructions for DET and repair of those
aeroplanes accordingly. Airbus developed mod 157335 to further
reinforce and adjust the affected rack fitting lugs. Analysis is
still ongoing to confirm mod 157335 as terminating action for the
requirements of this [EASA] AD, and further AD action may follow.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2015-0170, which is superseded, expanding
the Applicability to include post mod 35869 aeroplanes, and
requiring, for all aeroplanes, repetitive DET of the affected 10VU
rack fitting lugs and, depending on findings, accomplishment of a
repair [and reporting positive and negative findings to Airbus].
You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2018-
0903.
Comments
We 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.
Request To Allow Flight With Cracked 10VU Lug
JetBlue Airways requested that paragraph (i) of the proposed AD be
revised to allow flight with one cracked 10VU lug and to require repair
of that cracked 10VU lug prior to exceeding 5,000 flight cycles, 10,000
flight hours, or within 24 months after the effective date of the AD,
whichever occurred first. The commenter noted that paragraph (i) of the
proposed AD would require repair before further flight even if only one
10VU lug was cracked. The commenter stated that allowing flight with
one cracked 10VU lug would be in line with the requirements of EASA AD
2018-0131, dated June 19, 2018, and the procedures described in Airbus
Service Bulletin A320-92-1087, Revision 03, dated July 31, 2017; and
Airbus Service Bulletin A320-92-1119, dated July 28, 2017. The
commenter noted that if more than one 10VU lug was cracked then the
repair of all cracked 10VU lugs must be done before further flight.
We disagree with the commenter's request. As noted in the proposed
AD, we have determined that, because of the safety implications and
consequences associated with that cracking, any cracked 10VU rack
fitting lug must be repaired before further flight. Our general policy
does not allow flight with known cracks. This policy is based on the
fact that such damaged airplanes do not conform to the FAA-certificated
type design and, therefore, are not airworthy until a properly approved
repair is made. However, under the provisions of paragraph (m)(1) of
this AD, we will consider requests for approval of an extension of the
compliance time if sufficient data are submitted to substantiate that
the new compliance time would provide an acceptable level of safety, We
have not changed this AD regarding this issue.
Request To Clarify Testing Procedure Requirements
United Airlines (UAL) requested that the final AD include a
statement that the tests identified as ``Required for Compliance'' (RC)
in Airbus Service Bulletin A320-92-1087, Revision 03, dated July 31,
2017 (``A320-92-1087, Revision 03''); and Airbus Service Bulletin A320-
92-1119, dated July 28, 2017 (``A320-92-1119''), are only applicable if
the component identified in the test was removed and re-installed in
the airplane. The commenter suggested that the final AD allow operators
to conduct tests only on components that were removed so operators
could get access to the areas required to do the inspections.
The commenter noted that Airbus Service Bulletin A320-92-1087,
Revision 03, subtask 921087-700-002-001, ``Testing,'' provides a list
of components to be tested, but includes a statement that the required
testing is dependent upon which components were removed for access to
do an inspection and then re-installed on the airplane. The commenter
stated that Airbus Service Bulletin A320-92-1119 does not include such
a statement. The commenter explained that having this statement is
important because not every component listed is installed on every 10VU
rack, therefore operators could not do a test on a component that was
never installed, and including this statement would account for
different avionics equipment configurations within the 10VU rack. The
commenter provided the example that some UAL airplanes are not equipped
with angle-of-attack indicators or an integrated stand instrument
system, therefore the required tests could not be accomplished for
these components.
We agree with the intent of the commenter's request and we will
provide clarification regarding the RC tests. The intent of the RC
tests in the Airbus service information is to require testing of
equipment that was removed for access to do an inspection and then re-
installed in the airplane. The Airbus service information includes this
explanation regarding required testing in different locations. Airbus
Service Bulletin A320-92-1087, Revision 03, paragraph 3.D.(2),
``Subtask 921087-700-002-001, Testing,'' includes a statement that the
testing is dependent upon which components were removed in order to do
an inspection and are being re-installed on the airplane. The location
of this statement in Airbus Service Bulletin A320-92-1119, paragraph
3.D.(2), ``Subtask 921119-710-001-001, Testing,'' is in a note, which
states that ``The test procedure is to be accomplished after the
installation of the equipment removed for access . . . .'' This note
has the same intent as the statement and operators are not expected to
do testing on components that were never installed in the 10VU rack;
operators only have to test components that were removed and then re-
installed. We have not changed this AD regarding this issue.
[[Page 16388]]
Request To Refer to Current Service Information
UAL requested that, prior to publication of the final AD, we verify
that the current published revision level of Airbus Service Bulletin
A320-92-1087 and Airbus Service Bulletin A320-92-1119 are referred to
in the final AD. The comment stated that this would avoid the need to
apply for an alternative method of compliance (AMOC) immediately after
publication of the final AD.
We agree with the commenter's request and we have verified that
Airbus Service Bulletin A320-92-1087, Revision 03; and Airbus Service
Bulletin A320-92-1119; are the current published revision levels of
these documents. We have not changed this AD regarding this issue.
Request To Revise Reporting Method
JetBlue Airways requested that paragraph (j) of the proposed AD be
revised to remove the reference to the Airbus Service Bulletin
Reporting Online Application on Airbus World (https://w3.airbus.com/).
The commenter advocated that operators should be allowed to report
their findings to Airbus using a method of their choosing and that the
proposed AD should not specify how operators should report their
findings.
We agree to clarify. Paragraph (j) of this AD does not require
operators to report their findings using only the Airbus Service
Bulletin Reporting Online Application. Paragraph (j) of this AD
provides operators with the option of either using the Airbus Service
Bulletin Reporting Online Application or submitting the results to
Airbus in accordance with the instructions of Airbus Service Bulletin
A320-92-1087, Revision 03 (for Group 1 airplanes); or Airbus Service
Bulletin A320-92-1119 (for Group 2 airplanes); as applicable. We have
not changed this AD regarding this issue.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule as proposed, except for minor editorial changes. We
have 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.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletins A320-92-1087, Revision 03,
dated July 31, 2017; and A320-92-1119, dated July 28, 2017. This
service information describes procedures for repetitive inspections for
cracking of the 10VU rack fitting lugs, and repair of any cracking.
These documents are distinct since they apply to airplanes in different
configurations.
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.
Costs of Compliance
We estimate that this AD affects 461 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
2 work-hours x $85 per hour = $170........................... $0 $170 $78,370
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We estimate that it would take about 1 work-hour per product to
comply with the reporting requirement in this AD. The average labor
rate is $85 per hour. Based on these figures, we estimate the cost of
reporting the inspection results on U.S. operators to be $85 per
product.
We estimate the following costs to do any necessary repairs 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
repairs:
Estimated Costs of On-Condition Actions
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Cost per
Labor cost Parts cost product
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83 work-hours x $85 per hour = $7,055. $9,140 $16,195
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Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
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
[[Page 16389]]
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
We determined that 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 the 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 removing Airworthiness Directive (AD)
2016-19-14, Amendment 39-18663 (81 FR 71602, October 18, 2016), and
adding the following new AD:
2019-07-05 Airbus SAS: Amendment 39-19616; Docket No. FAA-2018-0903;
Product Identifier 2018-NM-113-AD.
(a) Effective Date
This AD is effective May 24, 2019.
(b) Affected ADs
This AD replaces AD 2016-19-14, Amendment 39-18663 (81 FR 71602,
October 18, 2016) (``AD 2016-19-14'').
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A318-111, -112, -121, and -122 airplanes.
(2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133
airplanes.
(3) Model A320-211, -212, -214, -216, -231, -232, and -233
airplanes.
(4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 92, Electric and
Electronic Common Installation.
(e) Reason
This AD was prompted by a report of cracks found during
maintenance inspections on certain 10VU rack fitting lugs. We are
issuing this AD to address reading difficulties of flight-critical
information displayed to the flightcrew during a critical phase of
flight, such as an approach or takeoff, which could result in loss
of airplane control at an altitude insufficient for recovery.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Definitions
For the purpose of this AD, Group 1 airplanes are in a pre-
Airbus Modification 35869 configuration, and Group 2 airplanes are
in a post-Airbus Modification 35869 configuration.
(h) Repetitive Inspections
(1) For Group 1 airplanes: At the later of the times specified
in table 1 to paragraph (h)(1) of this AD, and thereafter at
intervals not to exceed 20,000 flight cycles or 40,000 flight hours,
whichever occurs first, do a detailed inspection for cracking of the
10VU rack fitting lugs, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-92-1087, Revision 03,
dated July 31, 2017.
[GRAPHIC] [TIFF OMITTED] TR19AP19.000
(2) For Group 2 airplanes: At the later of the times specified
in paragraphs (h)(2)(i) and (h)(2)(ii) of this AD, and thereafter at
intervals not to exceed 20,000 flight cycles or 40,000 flight hours,
whichever occurs first, do a detailed inspection for cracking of the
10VU rack fitting lugs, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-92-1119, dated July 28,
2017.
(i) Prior to exceeding 30,000 total flight cycles or 60,000
total flight hours, whichever occurs first.
(ii) Within 30 days after the effective date of this AD.
(i) Repair
If any crack is found during any inspection required by
paragraph (h)(1) or (h)(2) of this AD: Before further flight, do a
repair in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-92-1087, Revision 03, dated July 31, 2017 (for
Group 1 airplanes); or Service Bulletin A320-92-1119, dated July 28,
2017 (for Group 2 airplanes); as applicable. Repair of a 10VU rack
fitting lug does not terminate the repetitive inspections required
by paragraphs (h)(1) and (h)(2) of this AD.
[[Page 16390]]
(j) Reporting
At the applicable time specified in paragraph (j)(1) or (j)(2)
of this AD: Submit a report of findings (positive and negative) of
each inspection required by paragraph (h) of this AD to Airbus
Service Bulletin Reporting Online Application on Airbus World
(https://w3.airbus.com/), or submit the results to Airbus in
accordance with the instructions of Airbus Service Bulletin A320-92-
1087, Revision 03, dated July 31, 2017 (for Group 1 airplanes); or
Service Bulletin A320-92-1119, dated July 28, 2017 (for Group 2
airplanes); as applicable. Where Figure A-FAAAA, Sheet 02, of
Appendix 01, ``Inspection Report,'' of Airbus Service Bulletin A320-
92-1087, Revision 03, dated July 31, 2017; and Figure A-FAAAA, Sheet
02, of Appendix 01, ``Inspection Report,'' of Service Bulletin A320-
92-1119, dated July 28, 2017; specifies sending removed lugs to
Airbus for investigation, this AD does not include that requirement.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 90 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 90 days after the effective date of
this AD.
(k) Credit for Previous Actions
This paragraph provides credit for actions required by
paragraphs (h)(1) and (i) of this AD if those actions were performed
before the effective date of this AD using Airbus Service Bulletin
A320-92-1087, Revision 02, dated November 25, 2014.
(l) Paperwork Reduction Act Burden Statement
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to a penalty
for failure to comply with a collection of information subject to
the requirements of the Paperwork Reduction Act unless that
collection of information displays a current valid OMB Control
Number. The OMB Control Number for this information collection is
2120-0056. Public reporting for this collection of information is
estimated to be approximately 1 hour per response, including the
time for reviewing instructions, completing and reviewing the
collection of information. All responses to this collection of
information are mandatory. Comments concerning the accuracy of this
burden and suggestions for reducing the burden should be directed to
the FAA at: 800 Independence Ave. SW, Washington, DC 20591, Attn:
Information Collection Clearance Officer, AES-200.
(m) Other FAA AD Provisions
(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 (n)(2) of this AD. Information
may be emailed to: [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: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (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): If any service information
contains procedures or tests that are identified as RC, those
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.
(n) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0131, dated June 19, 2018, for related
information. This MCAI may be found in the AD docket on the internet
at http://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0903.
(2) 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.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (o)(3) and (o)(4) of this AD.
(o) 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) Airbus Service Bulletin A320-92-1087, Revision 03, dated
July 31, 2017.
(ii) Airbus Service Bulletin A320-92-1119, dated July 28, 2017.
(3) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; internet
http://www.airbus.com.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on April 9, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-07940 Filed 4-18-19; 8:45 am]
BILLING CODE 4910-13-P