Airworthiness Directives; Airbus SAS Airplanes, 23461-23468 [2019-10653]
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Federal Register / Vol. 84, No. 99 / Wednesday, May 22, 2019 / Rules and Regulations
(h) Required Actions for Groups 1 Through
4 Airplanes
Except as specified by paragraph (j) of this
AD, for airplanes identified as Groups 1
through 4 in Boeing Alert Service Bulletin
737–30A1064, Revision 1, dated October 18,
2017: At the applicable times specified in
paragraph 1.E., ‘‘Compliance,’’ of Boeing
Alert Service Bulletin 737–30A1064,
Revision 1, dated October 18, 2017, do all
applicable actions identified as ‘‘RC’’
(required for compliance) in, and in
accordance with, the Accomplishment
Instructions of Boeing Alert Service Bulletin
737–30A1064, Revision 1, dated October 18,
2017.
(i) Concurrent Requirements
For airplanes identified as Groups 1
through 4 in Boeing Alert Service Bulletin
737–30A1064, Revision 1, dated October 18,
2017: Prior to or concurrently with the action
required by paragraph (h) of this AD, install
a new J18 junction box to change the antiicing system, in accordance with the
Accomplishment Instructions of Boeing
Service Bulletin 737–30–1067, Revision 1,
dated May 4, 2017, and install wiring
provisions to the anti-icing system, in
accordance with the Accomplishment
Instructions of Boeing Service Bulletin 737–
30–1068, Revision 1, dated May 4, 2017.
(j) Exceptions to Service Information
Specifications
For purposes of determining compliance
with the requirements of this AD: Where
Boeing Alert Service Bulletin 737–30A1064,
Revision 1, dated October 18, 2017, uses the
phrase ‘‘the original issue date of this service
bulletin,’’ this AD requires using ‘‘the
effective date of this AD.’’
(k) Credit for Previous Actions
This paragraph provides credit for the
actions specified in paragraph (h) of this AD,
if those actions were performed before the
effective date of this AD using Boeing Alert
Service Bulletin 737–30A1064, dated May 4,
2017, provided that step 15 for Groups 1
through 4 airplanes, as applicable, of the
Accomplishment Instructions of Boeing Alert
Service Bulletin 737–30A1064, Revision 1,
dated October 18, 2017, is done at the
applicable times specified in paragraph 1.E.,
‘‘Compliance,’’ of Boeing Alert Service
Bulletin 737–30A1064, Revision 1, dated
October 18, 2017, or within 180 days after the
effective date of this AD, whichever occurs
later.
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(l) Minimum Equipment List (MEL)
In the event that the air data probe heat
(ADPH) system as modified by this AD is
inoperable, an airplane may be operated as
specified in the operator’s MEL, provided the
MEL includes provisions that address the
modified ADPH system.
(m) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles ACO 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
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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 (n)(2) of
this AD. Information may be emailed to: 9ANM-LAACO-AMOC-Requests@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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO Branch, FAA, to make those findings.
To be approved, the repair method,
modification deviation, or alteration
deviation must meet the certification basis of
the airplane, and the approval must
specifically refer to this AD.
(4) For service information that contains
steps that are labeled as RC, the provisions
of paragraphs (m)(4)(i) and (m)(4)(ii) of this
AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled as RC may be
deviated from using accepted methods in
accordance with the operator’s maintenance
or inspection program without obtaining
approval of an AMOC, provided the RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
(n) Related Information
(1) For more information about this AD,
contact Frank Carreras, Aerospace Engineer,
Systems and Equipment Section, FAA,
Seattle ACO Branch, 2200 South 216th St.,
Des Moines, WA 98198; phone and fax: 206–
231–3539; email: frank.carreras@faa.gov.
(2) For information about AMOCs, contact
Jeffrey W. Palmer, Aerospace Engineer,
Systems and Equipment Section, FAA, Los
Angeles ACO Branch, 3960 Paramount
Boulevard, Lakewood, CA 90712–4137;
phone: 562–627–5851; fax: 562–627–5210;
email: jeffrey.w.palmer@faa.gov.
(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 the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 737–
30A1064, Revision 1, dated October 18, 2017.
(ii) Boeing Service Bulletin 737–30–1067,
Revision 1, dated May 4, 2017.
(iii) Boeing Service Bulletin 737–30–1068,
Revision 1, dated May 4, 2017.
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(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Contractual & Data
Services (C&DS), 2600 Westminster Blvd.,
MC 110–SK57, Seal Beach, CA 90740–5600;
telephone 562–797–1717; internet https://
www.myboeingfleet.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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on May
9, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–10657 Filed 5–21–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0795; Product
Identifier 2018–NM–076–AD; Amendment
39–19628; AD 2019–08–07]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–20–
04, which applied to all Airbus SAS
Model A318 and A319 series airplanes;
Airbus SAS Model A320–111, –211,
–212, –214, –231, –232, and –233
airplanes; and Airbus SAS Model A321–
111, –112, –131, –211, –212, –213, –231,
and –232 airplanes. AD 2014–20–04
required repetitive inspections of the
titanium angles between the belly
fairing and the keel beam side panel, an
inspection of the open holes of cracked
titanium angles, and corrective action if
necessary. This AD continues to require
those actions, adds Model A320–216
airplanes, and requires a detailed
inspection for, and replacement of,
certain rivets, and corrective actions if
necessary. This AD was prompted by
reports of cracks at the lower riveting of
the four titanium angles that connect the
belly fairing to the keel beam side
SUMMARY:
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Federal Register / Vol. 84, No. 99 / Wednesday, May 22, 2019 / Rules and Regulations
panels. We are issuing this AD to
address the unsafe condition on these
products.
DATES: This AD is effective June 26,
2019.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 26, 2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain other publication listed in
this AD as of November 7, 2014 (79 FR
59636, October 3, 2014).
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; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 44
51; email: account.airworth-eas@
airbus.com; internet: https://
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
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0795.
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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–
0795; 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;
phone 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 2014–20–04,
Amendment 39–17977 (79 FR 59636,
October 3, 2014) (‘‘AD 2014–20–04’’).
AD 2014–20–04 applied to all Airbus
SAS Model A318 series airplanes;
Airbus SAS Model A319 series
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airplanes; Airbus SAS Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Airbus SAS Model A321–
111, –112, –131, –211, –212, –213, –231,
and –232 airplanes. The NPRM
published in the Federal Register on
September 17, 2018 (83 FR 46905). The
NPRM was prompted by our
determination that additional work is
necessary for certain airplanes. The
NPRM proposed to continue to require
repetitive inspections for cracking of the
four titanium angles between the belly
fairing and the keel beam side panel, an
inspection for cracking of the open
holes if any cracking is found in the
titanium angles, and repair or
replacement if necessary. The NPRM
also proposed to revise the applicability
by adding Model A320–216 airplanes.
The NPRM also proposed additional
work, including a detailed inspection
for, and replacement of, certain rivets
(including a rotating probe test for
cracks in the open holes), and corrective
actions if necessary. We are issuing this
AD to address cracking at the lower
riveting of the four titanium angles that
connect the belly fairing to the keel
beam side panels on both sides of the
fuselage, which could affect the
structural integrity of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2018–0091,
dated April 20, 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 series
airplanes; Airbus SAS Model A319
series airplanes; Airbus SAS Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Airbus
SAS Model A321–111, –112, –131,
–211, –212, –213, –231, and –232
airplanes. The MCAI states:
During the fatigue test campaign of the
A320 family type design, cracks were found
at the lower riveting of the four titanium
angles which connect the belly fairing to the
keel beam side panels between frames FR40
and FR42, on both sides of the fuselage.
This condition, if not detected and
corrected, could affect the structural integrity
of the aeroplane.
To address this potential unsafe condition,
Airbus issued Service Bulletin (SB) A320–
53–1014, and DGAC [Direction Ge´ne´rale de
l’Aviation Civile] France issued AD 92–201–
030 [which corresponds to FAA AD 94–12–
03, Amendment 39–8930 (59 FR 28763, June
3, 1994) (‘‘AD 94–12–03’’)] to require
reinforcement of the belly fairing structure.
Following new investigation which
showed that these measures addressed only
part of the unsafe condition, Airbus
published SB A320–53–1259 and EASA
issued AD 2013–0122 [which corresponds to
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FAA AD 2014–20–04], retaining the
requirements of DGAC France AD 92–201–
030, which was superseded, and requiring
repetitive detailed inspections (DET) of the
affected titanium angles and, depending on
findings, repair or replacement of parts.
After that [EASA] AD was issued, Airbus
published Revision (Rev.) 01 and Rev. 02 of
SB A320–53–1259. [Airbus SB A320–53–
1259] Rev. 02 provided incorrect instructions
to use Part Number (P/N) EN6081D4 rivets
for the titanium angles installation, instead of
P/N EN6081D5 rivets. Consequently, Airbus
SB A320–53–1259 was updated (now at Rev.
03) including reference to the proper rivets.
For the reason described above, this
[EASA] AD retains the requirements of EASA
AD 2013–0122, which is superseded, and
requires additional work [a detailed
inspection for and replacement of certain
rivets, and applicable corrective actions] for
aeroplanes on which Airbus SB A320–53–
1259 at Rev. 02 was embodied.
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–
0795.
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 Withdraw the NPRM
Delta Air Lines (DAL) requested that
we re-issue the NPRM using the method
where the FAA AD would mandate the
EASA AD for compliance (i.e., the
‘‘incorporate by reference (IBR) the
MCAI’’ method). DAL pointed out this
method would simplify the
understanding of the NPRM and reduce
the number of conflicts between the
EASA AD and the NPRM.
We acknowledge the commenter’s
request to use the ‘‘IBR the MCAI’’
method. Using the ‘‘IBR the MCAI’’
method simplifies FAA ADs and
facilitates a simpler AD process.
However, we disagree with the request
to re-issue the NPRM using this method,
as it would require an additional public
comment period and unnecessarily
delay issuance of this final rule, which
is necessary to address the identified
unsafe condition. However, based on
positive feedback from operators, we are
expanding the use of the ‘‘IBR the
MCAI’’ method, and additional NPRMs
and ADs are currently being drafted
using this method.
Request To Use Previously Existing
Alternative Method of Compliance
(AMOC) for Compliance With This AD
DAL requested that we allow the use
of AMOC ANM–116–15–018 for
compliance with all corresponding
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provisions of the proposed AD. DAL
also requested that if the FAA disagrees
to include the use of the AMOC as
requested, that we include details in the
NPRM for addressing the airplanes
already inspected and modified using
the AMOC and Airbus Service Bulletin
A320–53–1259, Revision 01, dated
November 26, 2013. DAL mentioned
that several airplanes from the DAL fleet
were inspected and modified using the
AMOC and Airbus Service Bulletin
A320–53–1259, Revision 01, dated
November 26, 2013. DAL also pointed
out that the NPRM does not provide
credit for work performed using the
AMOC and Airbus Service Bulletin
A320–53–1259, Revision 01, dated
November 26, 2013.
We agree to allow the use of the
AMOC identified by the commenter, as
well as all other AMOCs to AD 2014–
20–04, and we have added paragraph
(r)(1)(ii) to this AD accordingly.
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Request To Use All Revisions of the
Service Information for Inspection
Compliance in Paragraph (h) of the
Proposed AD
DAL requested that we include Airbus
Service Bulletin A320–53–1259,
Revision 01, dated November 26, 2013,
and Airbus Service Bulletin A320–53–
1259, Revision 02, dated March 24,
2016, as service information for the
inspection requirements of the proposed
AD. DAL pointed out that the removal
and installation of the titanium angles is
the main concern in limiting the use of
Airbus Service Bulletin A320–53–1259,
Revision 02, dated March 24, 2016, but
that the inspection requirements contain
no errors. DAL also indicated
concurrence with the requirement to use
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
after the effective date of the final rule.
We agree for the reasons provided by
the commenter and have revised the
introductory text of paragraph (h) and
paragraphs (h)(2) and (k) of this AD
accordingly. However, we have only
revised paragraphs (i)(2), (j), and (l) of
this AD to include Airbus Service
Bulletin A320–53–1259, Revision 01,
dated November 26, 2013, because those
paragraphs include installation
requirements and Revision 02 of Airbus
Service Bulletin A320–53–1259 is not
acceptable service information for doing
those installations.
Request To Use Alternative Part
Number Titanium Angles
United Air Lines (UAL) requested that
we allow titanium angle part numbers
D5337060121295 and D5337060121495
to be installed instead of part numbers
D5337060121200 and D5337060121400,
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respectively. UAL stated that titanium
angle part numbers D5337060121200
and D5337060121400 as specified by
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
are not procurable. UAL mentioned that
Airbus indicated to UAL that titanium
angle part numbers D5337060121295
and D5337060121495 are acceptable for
installation for Airbus Service Bulletin
A320–53–1259, Revision 03, dated
November 30, 2017.
We agree with the commenter for the
reasons provided. We have added
paragraph (q) to this AD to allow the
installation of titanium angle part
numbers D5337060121295 and
D5337060121495. We have redesignated
subsequent paragraphs accordingly.
Request To Revise the Affected
Airplanes for Paragraph (o) of the
Proposed AD
DAL and UAL requested that we
revise the affected airplanes for
paragraph (o) of the proposed AD. UAL
requested that we clarify the service
information reference for description of
the affected airplanes in paragraph (o) of
the proposed AD. DAL and UAL
pointed out that the MCAI specifies
Revision 02 of Airbus Service Bulletin
A320–23–1259 for the action specified
in paragraph (o) of the proposed AD and
that paragraph (o) of the proposed AD
specifies Airbus Service Bulletin A320–
53–1259, dated November 6, 2012, for
identifying affected airplanes.
In addition, DAL requested that we
revise paragraph (o) of the proposed AD
to apply only to airplanes which had
titanium angles removed and replaced
in accordance with sub-task 531259–
203–001 of Airbus Service Bulletin
A320–53–1259, Revision 02, dated
March 24, 2016. DAL pointed out that
paragraph (o) of the proposed AD
specified airplanes which were
inspected using Airbus Service Bulletin
A320–53–1259, dated November 6,
2012. DAL mentioned that the unsafe
condition was introduced in Airbus
Service Bulletin A320–53–1259,
Revision 02, dated March 24, 2016, and
that there are no airworthiness concerns
with the inspections (only
replacements) accomplished under any
revision of the service information.
We agree that paragraph (o) of this AD
should refer to Airbus Service Bulletin
A320–53–1259, Revision 02, dated
March 24, 2016, to identify the affected
airplanes as specified in the MCAI, and
we have revised paragraph (o) of this
AD accordingly.
We also agree with the request to limit
the affected airplanes to those that had
titanium angles replaced in accordance
with sub-task 531259–203–001 of
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Airbus Service Bulletin A320–53–1259,
Revision 02, dated March 24, 2016.
However, we have determined that the
phrase ‘‘modified (replacement of
affected titanium angles),’’ which
matches the intent of the language in the
MCAI, is more appropriate instead of
listing specific sub-tasks for
replacement. Operators may have
installed these rivets in accordance with
instructions approved by Airbus SAS
under EASA’s Design Organization
Approval (DOA) outside of the service
information sub-task. Therefore, we
have not changed this AD further in this
regard.
Request for Clarification of Paragraph
(k) of the Proposed AD
UAL requested clarification of the
intent of paragraph (k) of the proposed
AD. UAL specified that the intent
should be a detailed inspection of the
‘‘replaced’’ titanium angles and not an
inspection of the four titanium angles.
UAL explained that paragraph (j) of the
proposed AD states to remove the
affected [cracked] titanium angle(s), and
the next inspection per paragraph (k) of
the proposed AD would apply to the
replaced titanium angles, not
necessarily all four titanium angles.
We agree for the reasons provided by
the commenter, and we have revised
paragraph (k) of this AD accordingly.
Request To Include Additional Data To
Correct an Error in the Service
Information
UAL requested that we include
information to correct an error in the
service information. UAL stated that
figure A–GCAAA Sheet 02 of Airbus
Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
shows views A–A and B–B in reversed
left and right direction and that view B–
B is missing one rivet location. UAL
also stated that this error makes it
possible to install incorrect rivets during
angle replacement. UAL mentioned that
it had contacted Airbus about this error,
and that Airbus published Technical
Adaptation 80491184/005/2018 to
temporarily correct the error. UAL also
mentioned that Airbus plans to revise
Service Bulletin A320–53–1259 to
correct this error.
We agree with the commenter’s
request for the reasons provided. To
ensure operators refer to the correct
views and rivet locations, we have
revised this AD by referencing Airbus
Technical Adaptation 80491184/005/
2018, Issue 1, dated February 08, 2018,
in lieu of Figure A GCAAA—Sheet 02
of Airbus Service Bulletin A320–53–
1259, Revision 03, dated November 30,
2017, wherever it is appropriate.
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Request To Verify the Required Service
Information Prior to AD Publication
Request for Clarification of Paragraph
(o) of the Proposed AD
UAL requested that we verify the
latest revision of Service Bulletin A320–
53–1259 is referenced in this AD prior
to final publication. UAL indicated its
preference not to request an AMOC
allowing use of a later revision of the
service information immediately after
AD publication.
We agree and have confirmed that
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
is the latest version of the service
information. We have not changed this
AD in this regard.
DAL requested that, to reduce
confusion, we include clarification in
paragraph (o) of the proposed AD, that
EN6081D5 rivets only need to be
installed in the fastener holes common
to the titanium angle and belly fairing
wall joint. DAL mentioned that
paragraph (o) of the proposed AD
provides relief for the on-wing
inspection if it can be determined no
titanium angles were installed in
accordance with Airbus Service Bulletin
A320–53–1259, Revision 02, dated
March 24, 2016, or if only EN6081D5
rivets were used to install the titanium
angles on that airplane. DAL pointed
out that the titanium angles are installed
using both hi-lok fasteners as well as
rivets. DAL also indicated that the hilok fasteners are common to the keel
beam panel and the rivets are common
to the belly fairing walls.
We agree to clarify. The service
information provides specific
information for a detailed inspection for
the rivets on the titanium angles and
belly fairing shear wall attachments
between frames (FR)40 and FR42.
Additionally, as specified previously,
Airbus has issued Airbus Technical
Adaptation 80491184/005/2018, Issue 1,
dated February 08, 2018, as an
exception to Figure A GCAAA—Sheet
02 of Airbus Service Bulletin A320–53–
1259, Revision 03, dated November 30,
2017, which we have included in this
AD. Therefore, in paragraph (o) of this
AD, where it specifies ‘‘or if only
EN6081D5 rivets were used to install
the titanium angles on that airplane,’’
the installation location for rivets is on
the titanium angles and belly fairing
shear wall attachments as identified in
the service information. Since the
service information provides this
information, we have not changed this
AD further regarding this issue.
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Request To Expand the Airplanes
Specified in Paragraph (o) of the
Proposed AD
UAL requested that we expand the
airplanes specified in paragraph (o) of
the proposed AD to include all angles
that were replaced using any service
information issued prior to Airbus
Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
unless maintenance records show that
the correct rivets were previously
installed. UAL pointed out that
revisions issued prior to Airbus Service
Bulletin A320–53–1259, Revision 02,
dated March 24, 2016, did not specify
any procedures to install rivets to the
keel beam side panel. UAL mentioned
that it could then be possible that an
angle replacement done previously
using Airbus Service Bulletin A320–53–
1259, dated November 6, 2012, or
Airbus Service Bulletin A320–53–1259,
Revision 01, dated November 26, 2013,
might have missing or incorrect rivets
installed.
We disagree with the request to
expand the affected airplanes specified
in paragraph (o) of this AD. As
discussed previously, we have clarified
that the affected airplanes specified in
paragraph (o) of this AD are those on
which a modification (replacement of
affected titanium angles) was done in
accordance with Airbus Service Bulletin
A320–53–1259, Revision 02, dated
March 24, 2016, and not airplanes on
which an inspection was done.
Additionally, we have not received any
information from either EASA or Airbus
regarding expanding the scope of the
potential unsafe condition. The new
requirements in this AD are a result of
incorrect dimensions of the rivet part
number provided in Airbus Service
Bulletin A320–53–1259, Revision 02,
dated March 24, 2016. No such
information was provided by Airbus in
the previous revisions of the service
information. We have not changed this
AD in this regard.
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Request To Use Additional Guidance
for Correct Fasteners
DAL requested that we include
additional guidance for accomplishing
the titanium angle replacement. DAL
stated that Airbus issued Operator
Information Telex (OIT) 16–0032, Rev.
00, dated June 3, 2016, that specified the
required rivets to use for the
replacement. DAL also mentioned that
Airbus issued Technical Adaptation
80170642/022/2017, dated April 7,
2017, to Airbus Service Bulletin A320–
53–1259, Revision 02, dated March 24,
2016, which specified the correct rivets
for the replacement. DAL added that the
FAA could provide credit for airplanes
on which the correct rivets were
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installed using the OIT or technical
adaptation.
We disagree with the request.
Paragraph (p)(2) of this AD refers to
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
and Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated
February 08, 2018, which provide
adequate service information for
completing the replacement required if
any part number EN6081D4 series rivet
is found during any inspection required
by paragraph (o) of this AD. This AD
corresponds to EASA AD 2018–0091,
dated April 20, 2018, which does not
permit Airbus OIT 16–0032, Rev. 00,
dated June 3, 2016, and Airbus
Technical Adaptation 80170642/022/
2017, dated April 7, 2017, as methods
of compliance. We agree that those
documents are not acceptable methods
of compliance with this AD because
those documents only specify the part
numbers as well as the location and
quantity of the parts.
However, we do agree to clarify the
statement in paragraph (o) of this AD
that describes a method of compliance
for the actions required by paragraph (o)
of this AD. Paragraph (o) of this AD
provides relief for airplanes on which
‘‘it can be determined that no titanium
angles have been installed on that
airplane in accordance with the
Accomplishment Instructions of
Revision 02 of Airbus Service Bulletin
A320–53–1259, or if only rivets having
part number EN6081D5 have been used
to install the titanium angles.’’ We have
revised paragraph (o) of this AD to
clarify that the ‘‘in accordance with the
Accomplishment Instructions of
Revision 02 of Airbus Service Bulletin
A320–53–1259’’ applies to the whole
statement.
Clarification of Retained Effective Date
for Paragraph (g) of This AD
In the introductory text of paragraph
(g) of the proposed AD we retained a
compliance time that referred to the
effective date of the existing AD.
However, we did not include the
specific date of AD 2014–20–04. We
have revised the introductory text of
paragraph (g) of this AD to refer to the
effective date of AD 2014–20–04
(November 7, 2014).
Clarification of Retained Effective Date
for Paragraph (h)(3) of This AD
In paragraph (h)(3) of the proposed
AD we retained a compliance time that
referred to the effective date of the
existing AD. However, we did not
include the effective date of AD 2014–
20–04. We have revised paragraph (h)(3)
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of this AD to refer to the effective date
of AD 2014–20–04 (November 7, 2014).
Related Service Information Under 1
CFR Part 51
Conclusion
We 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.
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.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this final rule.
Airbus has issued Service Bulletin
A320–53–1259, Revision 03, dated
November 30, 2017. This service
information describes procedures for
repetitive inspections for cracking of the
four titanium angles between the belly
fairing and the keel beam side panel, an
inspection for cracking of the open
holes if any cracking is found in the
titanium angles, repair or replacement if
necessary, and a detailed inspection for
and replacement of certain rivets
(including a rotating probe test for
cracks in the open holes).
Airbus has also issued Technical
Adaptation 80491184/005/2018, Issue 1,
dated February 08, 2018. This service
information describes a correction to
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017.
This AD also requires Airbus Service
Bulletin A320–53–1014, Revision 2,
dated September 1, 1994, which the
Director of the Federal Register
approved for incorporation by reference
as of November 7, 2014 (79 FR 59636,
October 3, 2014).
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 1,250
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Labor cost
Parts cost
295 work-hours × $85 per hour = $25,075 (Retained actions from AD
2014–20–04).
Up to 168 work-hours × $85 per hour = Up to $14,280 (New actions of this
AD).
We estimate the following costs to do
any necessary replacement that would
Cost per product
Cost on U.S. operators
$1,045
$26,120 ..................
$32,650,000.
0
Up to $14,280 ........
Up to $17,850,000.
be required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need this replacement:
ESTIMATED COSTS OF ON-CONDITION ACTIONS
Labor cost
Parts cost *
Cost per
product
168 work-hours × $85 per hour = $14,280 .............................................................................................................
$0
$14,280
* We have received no definitive data that would enable us to provide cost estimates for the on-condition parts costs.
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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.
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15:56 May 21, 2019
Jkt 247001
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.
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.
Regulatory Findings
List of Subjects in 14 CFR Part 39
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.
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
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Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
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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
removing Airworthiness Directive (AD)
2014–20–04, Amendment 39–17977 (79
FR 59636, October 3, 2014), and adding
the following new AD:
■
2019–08–07 Airbus SAS: Amendment 39–
19628; Docket No. FAA–2018–0795;
Product Identifier 2018–NM–076–AD.
(a) Effective Date
This AD is effective June 26, 2019.
(b) Affected ADs
This AD replaces AD 2014–20–04,
Amendment 39–17977 (79 FR 59636, October
3, 2014) (‘‘AD 2014–20–04’’).
(c) Applicability
This AD applies to the Airbus SAS
airplanes specified in paragraphs (c)(1),
(c)(2), (c)(3), and (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 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks
at the lower riveting of the four titanium
angles that connect the belly fairing to the
keel beam side panels on both sides of the
fuselage. We are issuing this AD to address
cracking of the titanium angles that connect
the belly fairing to the keel beam side panels
on both sides of the fuselage, which could
affect the structural integrity of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained Modification, With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2014–20–04, with no
changes. For Model A320–211 and –231
series airplanes, manufacturer serial numbers
003 through 092 inclusive: Prior to the
accumulation of 12,000 total landings on the
airplane, or within 300 days after January 10,
1994 (the effective date of AD 93–24–11,
Amendment 39–8760 (58 FR 64875,
December 10, 1993)), whichever occurs later,
modify the belly fairing structure, in
accordance with the Accomplishment
Instructions of an Airbus service bulletin
specified in paragraph (g)(1), (g)(2), or (g)(3)
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15:56 May 21, 2019
Jkt 247001
of this AD. As of November 7, 2014 (the
effective date of AD 2014–20–04), use only
the Airbus service bulletin specified in
paragraph (g)(3) of this AD.
(1) Airbus Industrie Service Bulletin A320–
53–1014, dated June 25, 1992.
(2) Airbus Industrie Service Bulletin A320–
53–1014, Revision 1, dated May 26, 1993.
(3) Airbus Service Bulletin A320–53–1014,
Revision 2, dated September 1, 1994.
(h) Retained Repetitive Inspection, With
Updated Service Information
This paragraph restates the requirements of
paragraph (h) of AD 2014–20–04, with
updated service information. At the latest of
the compliance times specified in paragraphs
(h)(1), (h)(2), and (h)(3) of this AD: Do a
detailed inspection for cracking of the four
titanium angles between the belly fairing and
the keel beam side panel, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, dated
November 6, 2012; Airbus Service Bulletin
A320–53–1259, Revision 01, dated November
26, 2013; Airbus Service Bulletin A320–53–
1259, Revision 02, dated March 24, 2016; or
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017. After
the effective date of this AD, only Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017, may be used.
Where Airbus Service Bulletin A320–53–
1259, Revision 03, dated November 30, 2017,
specifies to refer to Figure A GCAAA—Sheet
02, instead use Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated February
08, 2018.
(1) Before the accumulation of 30,000 total
flight cycles or 60,000 total flight hours,
whichever occurs first after first flight of the
airplane.
(2) Within 30,000 flight cycles or 60,000
flight hours, whichever occurs first after
modification of the airplane as required by
paragraph (g) of this AD, or after installation
of new titanium angles, provided that, prior
to installation, a rototest for cracking on the
open holes has been accomplished with no
crack findings, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, dated
November 6, 2012; Airbus Service Bulletin
A320–53–1259, Revision 01, dated November
26, 2013; Airbus Service Bulletin A320–53–
1259, Revision 02, dated March 24, 2016; or
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017. After
the effective date of this AD, only Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017, may be used.
Where Airbus Service Bulletin A320–53–
1259, Revision 03, dated November 30, 2017,
specifies to refer to Figure A GCAAA—Sheet
02, instead use Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated February
08, 2018.
(3) Within 3,000 flight cycles or 6,000
flight hours, whichever occurs first after
November 7, 2014 (the effective date of AD
2014–20–04).
(i) Retained Post-Inspection Actions for No
Crack Findings, With Updated Service
Information
This paragraph restates the requirements of
paragraph (i) of AD 2014–20–04, with
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Fmt 4700
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updated service information. If, during any
inspection required by paragraph (h) of this
AD, there is no crack finding: Accomplish
the actions specified in either paragraph (i)(1)
or (i)(2) of this AD.
(1) Repeat the inspection required by
paragraph (h) of this AD at intervals not to
exceed 5,000 flight cycles or 10,000 flight
hours, whichever occurs first.
(2) Before further flight after the inspection
required by paragraph (h) of this AD, remove
all inspected titanium angles, accomplish a
rototest for cracking on the open holes and,
provided no cracks are found, install new
titanium angles, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, dated
November 6, 2012; Airbus Service Bulletin
A320–53–1259, Revision 01, dated November
26, 2013; or Airbus Service Bulletin A320–
53–1259, Revision 03, dated November 30,
2017. After the effective date of this AD, only
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017, may
be used. Where Airbus Service Bulletin
A320–53–1259, Revision 03, dated November
30, 2017, specifies to refer to Figure A
GCAAA—Sheet 02, instead use Airbus
Technical Adaptation 80491184/005/2018,
Issue 1, dated February 08, 2018.
(j) Retained Post-Inspection Actions for Any
Crack Findings, With Updated Service
Information
This paragraph restates the requirements of
paragraph (j) of AD 2014–20–04, with
updated service information. If, during any
inspection required by paragraph (h) of this
AD, there is any crack finding: Before further
flight, remove the affected titanium angle(s),
accomplish a rototest for cracking on the
open holes, and, provided no cracks are
found, install new titanium angles, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1259, dated November 6, 2012; Airbus
Service Bulletin A320–53–1259, Revision 01,
dated November 26, 2013; or Airbus Service
Bulletin A320–53–1259, Revision 03, dated
November 30, 2017. After the effective date
of this AD, only Airbus Service Bulletin
A320–53–1259, Revision 03, dated November
30, 2017, may be used. Where Airbus Service
Bulletin A320–53–1259, Revision 03, dated
November 30, 2017, specifies to refer to
Figure A GCAAA—Sheet 02, instead use
Airbus Technical Adaptation 80491184/005/
2018, Issue 1, dated February 08, 2018.
(k) Retained Post-Installation Repetitive
Inspections, With Updated Service
Information and Revised Compliance
Language
This paragraph restates the requirements of
paragraph (k) of AD 2014–20–04, with
updated service information and revised
compliance language. For airplanes on which
new titanium angles were installed as
specified in paragraph (i)(2) or (j) of this AD:
Within 30,000 flight cycles or 60,000 flight
hours, whichever occurs first after the
installation, accomplish a detailed inspection
for cracking of the replaced titanium angles
between the belly fairing and the keel beam
side panel, in accordance with the
Accomplishment Instructions of Airbus
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Service Bulletin A320–53–1259, dated
November 6, 2012; Airbus Service Bulletin
A320–53–1259, Revision 01, dated November
26, 2013; Airbus Service Bulletin A320–53–
1259, Revision 02, dated March 24, 2016; or
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017. After
the effective date of this AD, only Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017, may be used.
Repeat the inspection thereafter at intervals
not to exceed 5,000 flight cycles or 10,000
flight hours, whichever occurs first. Where
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
specifies to refer to Figure A GCAAA—Sheet
02, instead use Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated February
08, 2018.
(l) Retained Post-Inspection Actions for Any
Crack Findings During Post-Installation
Inspections, With Updated Service
Information
This paragraph restates the requirements of
paragraph (l) of AD 2014–20–04, with
updated service information. If, during any
inspection as required by paragraph (k) of
this AD, there is any crack finding: Before
further flight, remove the affected titanium
angles, accomplish a rototest for cracking on
the open holes, and, provided no cracks are
found, install new titanium angles, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1259, dated November 6, 2012; Airbus
Service Bulletin A320–53–1259, Revision 01,
dated November 26, 2013; or Airbus Service
Bulletin A320–53–1259, Revision 03, dated
November 30, 2017. After the effective date
of this AD, only Airbus Service Bulletin
A320–53–1259, Revision 03, dated November
30, 2017, may be used. Where Airbus Service
Bulletin A320–53–1259, Revision 03, dated
November 30, 2017, specifies to refer to
Figure A GCAAA—Sheet 02, instead use
Airbus Technical Adaptation 80491184/005/
2018, Issue 1, dated February 08, 2018.
(n) Retained No Termination Action for
Repetitive Inspections, With No Changes
This paragraph restates the requirements of
paragraph (n) of AD 2014–20–04, with no
changes. Repair or replacement of parts as
specified in this AD does not terminate the
repetitive inspections required by this AD.
(p) New Requirements of This AD:
Replacement of Certain Rivets
If any part number EN6081D4 series rivet
is found during any inspection required by
paragraph (o) of this AD, before further flight,
do the actions specified in paragraphs (p)(1)
and (p)(2) of this AD.
(1) Remove the part number EN6081D4
series rivets and do a rotating probe test of
the open holes for cracks, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017. If any crack is
found during any inspection required by this
paragraph, before further flight, obtain
corrective actions approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus SAS’s
EASA DOA; and accomplish the corrective
actions within the compliance time specified
therein. If approved by the DOA, the
approval must include the DOA-authorized
signature.
(2) Replace part number EN6081D4 series
rivets with part number EN6081D5 series
rivets in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017. Where Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017, specifies to refer
to Figure A GCAAA—Sheet 02, instead use
Airbus Technical Adaptation 80491184/005/
2018, Issue 1, dated February 08, 2018.
(o) New Requirement of This AD: Detailed
Inspection for Certain Rivets
For airplanes previously modified
(replacement of affected titanium angles)
(q) Service Information Exception
Where the Accomplishment Instructions of
Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017,
(m) Retained Corrective Action for Rototest
Crack Finding, With Updated Contact
Information
This paragraph restates the requirements of
paragraph (m) of AD 2014–20–04, with
updated contact information. If, during any
rototest as required by paragraph (i), (j), or (l)
of this AD, any crack is found: Before further
flight, repair 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.
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using the Accomplishment Instructions of
Revision 02 of Airbus Service Bulletin A320–
53–1259: At the earlier of the times specified
in paragraphs (o)(1) and (o)(2) of this AD, do
a detailed inspection of the rivet installation
in the belly fairing shear walls and the
titanium angles for part number EN6081D4
series rivets in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017. A review of the
airplane maintenance records is acceptable to
comply with the requirements of this
paragraph for that airplane, provided it can
be determined that no titanium angles have
been installed on that airplane in accordance
with the Accomplishment Instructions of
Revision 02 of Airbus Service Bulletin A320–
53–1259, or if only rivets having part number
EN6081D5 have been used to install the
titanium angles on that airplane in
accordance with the Accomplishment
Instructions of Revision 02 of Airbus Service
Bulletin A320–53–1259. Where Airbus
Service Bulletin A320–53–1259, Revision 03,
dated November 30, 2017, specifies to refer
to Figure A GCAAA—Sheet 02, instead use
Airbus Technical Adaptation 80491184/005/
2018, Issue 1, dated February 08, 2018.
(1) Within 2,000 flight cycles or 4,000
flight hours, whichever occurs first after the
effective date of this AD.
(2) Before exceeding 5,000 flight cycles or
10,000 flight hours, whichever occurs first
after accomplishment of the last inspection
specified in paragraph (h) of this AD.
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15:56 May 21, 2019
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23467
specify to install titanium angle part numbers
D5337060121200 and D5337060121400, this
AD allows the installation of titanium angle
part numbers D5337060121295 and
D5337060121495, respectively.
(r) 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 (s)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2014–20–04, are approved as AMOCs for the
corresponding provisions of this AD.
(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 EASA; or Airbus
SAS’s EASA DOA. If approved by the DOA,
the approval must include the DOAauthorized 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.
(s) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0091, dated April 20, 2018, for related
information. This MCAI may be found in the
AD docket on the internet at https://
www.regulations.gov by searching for and
locating Docket No. FAA–2018–0795.
(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; phone and fax: 206–231–
3223.
(t) 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.
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(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on June 26, 2019.
(i) Airbus Service Bulletin A320–53–1259,
Revision 03, dated November 30, 2017.
(ii) Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated February
08, 2018. The date appears only on the last
page of the document.
(4) The following service information was
approved for IBR on November 7, 2014 (79
FR 59636, October 3, 2014).
(i) Airbus Service Bulletin A320–53–1014,
Revision 2, dated September 1, 1994,
including supplementary page 7A. Pages 1
through 3, 15, 19, 20, and 25 of this
document are identified as Revision 2, dated
September 1, 1994; pages 4 through 8, 10, 12,
16 through 18, and 21 through 24 are
identified as Revision 1, dated May 26, 1993;
and pages 9, 11, 13, 14, and 26 are identified
as the original, dated June 25, 1992.
(ii) [Reserved]
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone:
+33 5 61 93 36 96; fax: +33 5 61 93 44 51;
email: account.airworth-eas@airbus.com;
internet: https://www.airbus.com.
(6) 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.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
April 10, 2019.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2019–10653 Filed 5–21–19; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF COMMERCE
Bureau of Industry and Security
15 CFR Parts 744 and 762
[Docket No. 190513445–9459–02]
RIN 0694–AH86
Temporary General License
Bureau of Industry and
Security, Commerce.
ACTION: Final rule.
jbell on DSK3GLQ082PROD with RULES
AGENCY:
This final rule creates a 90day temporary general license that
partially restores the licensing
requirements and policies under the
SUMMARY:
VerDate Sep<11>2014
15:56 May 21, 2019
Jkt 247001
Export Administration Regulations
(EAR) for exports, reexports, and
transfers (in-country) to sixty-nine
entities added to the Entity List on May
16, 2019.
DATES: This rule is effective May 20,
2019, through August 19, 2019.
FOR FURTHER INFORMATION CONTACT:
Director, Office of Exporter Services,
Bureau of Industry and Security,
Department of Commerce, Phone: (949)
660–0144 or (408) 998–8806 or email
your inquiry to: ECDOEXS@bis.doc.gov.
SUPPLEMENTARY INFORMATION:
Background
The Entity List (Supplement No. 4 to
Part 744) identifies entities and other
persons reasonably believed to be
involved, or to pose a significant risk of
being or becoming involved, in
activities contrary to the national
security or foreign policy interests of the
United States. The End-User Review
Committee (ERC), composed of
representatives of the Departments of
Commerce (Chair), State, Defense,
Energy and, where appropriate, the
Treasury, makes all decisions regarding
additions to, removals from, or other
modifications to the Entity List. The
ERC makes all decisions to add an entry
to the Entity List by majority vote and
all decisions to remove or modify an
entry by unanimous vote.
This final rule does not amend the
Entity List, but modifies the license
requirement for the sixty-nine entries
added to the Entity List in the May 16,
2019, final rule entitled ‘‘Addition of
Entities to the Entity List,’’ as described
further below, by adding a temporary
general license for the specified entities.
Addition of Huawei Technologies Co.,
Ltd. and Sixty-Eight Related Entities to
the Entity List
BIS added Huawei Technologies Co.,
Ltd. (Huawei) and sixty-eight of its nonU.S. affiliates to the Entity List on May
16, 2019. Details regarding the scope of
the listing are in the final rule titled
‘‘Addition to the Entity List,’’ effective
May 16, 2019, and scheduled to publish
in the May 21, 2019, issue of the
Federal Register. The sixty-eight nonU.S. affiliates are also listed in
Supplement No. 7 to part 744—
Temporary General License.
Addition of Temporary General License
This final rule amends the EAR by
adding Supplement No. 7 to Part 744 to
create a Temporary General License that
returns in part the prior requirements
through August 14, 2019. In this final
rule, pursuant to Supplement No. 5 to
part 744 of the Export Administration
PO 00000
Frm 00030
Fmt 4700
Sfmt 4700
Regulations (EAR), BIS is modifying the
effect of the sixty-nine entries on the
Entity List by adding a temporary
general license to temporarily authorize,
as specified below, engagement in
transactions, involving the export,
reexport, and transfer (in-country) of
items subject to the EAR to Huawei and
its sixty-eight non-U.S. affiliates subject
to the conditions described below.
a. This temporary general license is
effective from the date of this
Authorization, May 20, 2019, through
August 19, 2019.
b. This temporary general license does
not relieve persons of other obligations
under the EAR, including but not
limited to licensing requirements to the
People’s Republic of China (PRC or
China) or elsewhere and/or the
requirements of part 744 of the EAR.
This authorization does not authorize
any activities or transactions involving
Country Group E countries (i.e., Cuba,
Iran, North Korea, Sudan, and Syria) or
persons.
c. With the exception of the
transactions explicitly authorized by
this temporary general license, exports,
reexports, and transfers (in-country)
continue to require a license pursuant to
the license requirement set forth in
Supplement No. 4 to part 744 for
Huawei and the sixty-eight non-U.S.
affiliates and will be reviewed under the
license review policy for those entities.
This temporary general license
allows, from May 20, 2019, through
August 19, 2019, the following:
1. Continued Operation of Existing
Networks and Equipment: BIS
authorizes engagement in transactions,
subject to other provisions of the EAR,
necessary to maintain and support
existing and currently fully operational
networks and equipment, including
software updates and patches, subject to
legally binding contracts and
agreements executed between Huawei
and third parties or the sixty-eight nonU.S. Huawei affiliates and third parties
on or before May 16, 2019.
2. Support to Existing Handsets: BIS
authorizes engagement in transactions,
subject to other provisions of the EAR,
necessary to provide service and
support, including software updates or
patches, to existing Huawei handsets
that were available to the public on or
before May 16, 2019.
3. Cybersecurity Research and
Vulnerability Disclosure: BIS authorizes,
subject to other provisions of the EAR,
the disclosure to Huawei and/or the
sixty-eight non-U.S. affiliates of
information regarding security
vulnerabilities in items owned,
possessed, or controlled by Huawei or
any of the sixty-eight non-U.S. affiliates
E:\FR\FM\22MYR1.SGM
22MYR1
]]>Agencies
[Federal Register Volume 84, Number 99 (Wednesday, May 22, 2019)]
[Rules and Regulations]
[Pages 23461-23468]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-10653]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD; Amendment
39-19628; AD 2019-08-07]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2014-20-04,
which applied to all Airbus SAS Model A318 and A319 series airplanes;
Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and -233
airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213,
-231, and -232 airplanes. AD 2014-20-04 required repetitive inspections
of the titanium angles between the belly fairing and the keel beam side
panel, an inspection of the open holes of cracked titanium angles, and
corrective action if necessary. This AD continues to require those
actions, adds Model A320-216 airplanes, and requires a detailed
inspection for, and replacement of, certain rivets, and corrective
actions if necessary. This AD was prompted by reports of cracks at the
lower riveting of the four titanium angles that connect the belly
fairing to the keel beam side
[[Page 23462]]
panels. We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective June 26, 2019.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 26,
2019.
The Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD as of
November 7, 2014 (79 FR 59636, October 3, 2014).
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; phone: +33 5 61 93 36 96;
fax: +33 5 61 93 44 51; email: [email protected];
internet: https://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 https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0795.
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-
0795; 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; phone 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 2014-20-04, Amendment 39-17977 (79 FR 59636,
October 3, 2014) (``AD 2014-20-04''). AD 2014-20-04 applied to all
Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series
airplanes; Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and
-233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212,
-213, -231, and -232 airplanes. The NPRM published in the Federal
Register on September 17, 2018 (83 FR 46905). The NPRM was prompted by
our determination that additional work is necessary for certain
airplanes. The NPRM proposed to continue to require repetitive
inspections for cracking of the four titanium angles between the belly
fairing and the keel beam side panel, an inspection for cracking of the
open holes if any cracking is found in the titanium angles, and repair
or replacement if necessary. The NPRM also proposed to revise the
applicability by adding Model A320-216 airplanes. The NPRM also
proposed additional work, including a detailed inspection for, and
replacement of, certain rivets (including a rotating probe test for
cracks in the open holes), and corrective actions if necessary. We are
issuing this AD to address cracking at the lower riveting of the four
titanium angles that connect the belly fairing to the keel beam side
panels on both sides of the fuselage, which could affect the structural
integrity of the airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2018-0091, dated April 20, 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 series
airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model
A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Airbus
SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232
airplanes. The MCAI states:
During the fatigue test campaign of the A320 family type design,
cracks were found at the lower riveting of the four titanium angles
which connect the belly fairing to the keel beam side panels between
frames FR40 and FR42, on both sides of the fuselage.
This condition, if not detected and corrected, could affect the
structural integrity of the aeroplane.
To address this potential unsafe condition, Airbus issued
Service Bulletin (SB) A320-53-1014, and DGAC [Direction
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 92-
201-030 [which corresponds to FAA AD 94-12-03, Amendment 39-8930 (59
FR 28763, June 3, 1994) (``AD 94-12-03'')] to require reinforcement
of the belly fairing structure.
Following new investigation which showed that these measures
addressed only part of the unsafe condition, Airbus published SB
A320-53-1259 and EASA issued AD 2013-0122 [which corresponds to FAA
AD 2014-20-04], retaining the requirements of DGAC France AD 92-201-
030, which was superseded, and requiring repetitive detailed
inspections (DET) of the affected titanium angles and, depending on
findings, repair or replacement of parts.
After that [EASA] AD was issued, Airbus published Revision
(Rev.) 01 and Rev. 02 of SB A320-53-1259. [Airbus SB A320-53-1259]
Rev. 02 provided incorrect instructions to use Part Number (P/N)
EN6081D4 rivets for the titanium angles installation, instead of P/N
EN6081D5 rivets. Consequently, Airbus SB A320-53-1259 was updated
(now at Rev. 03) including reference to the proper rivets.
For the reason described above, this [EASA] AD retains the
requirements of EASA AD 2013-0122, which is superseded, and requires
additional work [a detailed inspection for and replacement of
certain rivets, and applicable corrective actions] for aeroplanes on
which Airbus SB A320-53-1259 at Rev. 02 was embodied.
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-
0795.
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 Withdraw the NPRM
Delta Air Lines (DAL) requested that we re-issue the NPRM using the
method where the FAA AD would mandate the EASA AD for compliance (i.e.,
the ``incorporate by reference (IBR) the MCAI'' method). DAL pointed
out this method would simplify the understanding of the NPRM and reduce
the number of conflicts between the EASA AD and the NPRM.
We acknowledge the commenter's request to use the ``IBR the MCAI''
method. Using the ``IBR the MCAI'' method simplifies FAA ADs and
facilitates a simpler AD process. However, we disagree with the request
to re-issue the NPRM using this method, as it would require an
additional public comment period and unnecessarily delay issuance of
this final rule, which is necessary to address the identified unsafe
condition. However, based on positive feedback from operators, we are
expanding the use of the ``IBR the MCAI'' method, and additional NPRMs
and ADs are currently being drafted using this method.
Request To Use Previously Existing Alternative Method of Compliance
(AMOC) for Compliance With This AD
DAL requested that we allow the use of AMOC ANM-116-15-018 for
compliance with all corresponding
[[Page 23463]]
provisions of the proposed AD. DAL also requested that if the FAA
disagrees to include the use of the AMOC as requested, that we include
details in the NPRM for addressing the airplanes already inspected and
modified using the AMOC and Airbus Service Bulletin A320-53-1259,
Revision 01, dated November 26, 2013. DAL mentioned that several
airplanes from the DAL fleet were inspected and modified using the AMOC
and Airbus Service Bulletin A320-53-1259, Revision 01, dated November
26, 2013. DAL also pointed out that the NPRM does not provide credit
for work performed using the AMOC and Airbus Service Bulletin A320-53-
1259, Revision 01, dated November 26, 2013.
We agree to allow the use of the AMOC identified by the commenter,
as well as all other AMOCs to AD 2014-20-04, and we have added
paragraph (r)(1)(ii) to this AD accordingly.
Request To Use All Revisions of the Service Information for Inspection
Compliance in Paragraph (h) of the Proposed AD
DAL requested that we include Airbus Service Bulletin A320-53-1259,
Revision 01, dated November 26, 2013, and Airbus Service Bulletin A320-
53-1259, Revision 02, dated March 24, 2016, as service information for
the inspection requirements of the proposed AD. DAL pointed out that
the removal and installation of the titanium angles is the main concern
in limiting the use of Airbus Service Bulletin A320-53-1259, Revision
02, dated March 24, 2016, but that the inspection requirements contain
no errors. DAL also indicated concurrence with the requirement to use
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30,
2017, after the effective date of the final rule.
We agree for the reasons provided by the commenter and have revised
the introductory text of paragraph (h) and paragraphs (h)(2) and (k) of
this AD accordingly. However, we have only revised paragraphs (i)(2),
(j), and (l) of this AD to include Airbus Service Bulletin A320-53-
1259, Revision 01, dated November 26, 2013, because those paragraphs
include installation requirements and Revision 02 of Airbus Service
Bulletin A320-53-1259 is not acceptable service information for doing
those installations.
Request To Use Alternative Part Number Titanium Angles
United Air Lines (UAL) requested that we allow titanium angle part
numbers D5337060121295 and D5337060121495 to be installed instead of
part numbers D5337060121200 and D5337060121400, respectively. UAL
stated that titanium angle part numbers D5337060121200 and
D5337060121400 as specified by Airbus Service Bulletin A320-53-1259,
Revision 03, dated November 30, 2017, are not procurable. UAL mentioned
that Airbus indicated to UAL that titanium angle part numbers
D5337060121295 and D5337060121495 are acceptable for installation for
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30,
2017.
We agree with the commenter for the reasons provided. We have added
paragraph (q) to this AD to allow the installation of titanium angle
part numbers D5337060121295 and D5337060121495. We have redesignated
subsequent paragraphs accordingly.
Request To Revise the Affected Airplanes for Paragraph (o) of the
Proposed AD
DAL and UAL requested that we revise the affected airplanes for
paragraph (o) of the proposed AD. UAL requested that we clarify the
service information reference for description of the affected airplanes
in paragraph (o) of the proposed AD. DAL and UAL pointed out that the
MCAI specifies Revision 02 of Airbus Service Bulletin A320-23-1259 for
the action specified in paragraph (o) of the proposed AD and that
paragraph (o) of the proposed AD specifies Airbus Service Bulletin
A320-53-1259, dated November 6, 2012, for identifying affected
airplanes.
In addition, DAL requested that we revise paragraph (o) of the
proposed AD to apply only to airplanes which had titanium angles
removed and replaced in accordance with sub-task 531259-203-001 of
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24,
2016. DAL pointed out that paragraph (o) of the proposed AD specified
airplanes which were inspected using Airbus Service Bulletin A320-53-
1259, dated November 6, 2012. DAL mentioned that the unsafe condition
was introduced in Airbus Service Bulletin A320-53-1259, Revision 02,
dated March 24, 2016, and that there are no airworthiness concerns with
the inspections (only replacements) accomplished under any revision of
the service information.
We agree that paragraph (o) of this AD should refer to Airbus
Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016, to
identify the affected airplanes as specified in the MCAI, and we have
revised paragraph (o) of this AD accordingly.
We also agree with the request to limit the affected airplanes to
those that had titanium angles replaced in accordance with sub-task
531259-203-001 of Airbus Service Bulletin A320-53-1259, Revision 02,
dated March 24, 2016. However, we have determined that the phrase
``modified (replacement of affected titanium angles),'' which matches
the intent of the language in the MCAI, is more appropriate instead of
listing specific sub-tasks for replacement. Operators may have
installed these rivets in accordance with instructions approved by
Airbus SAS under EASA's Design Organization Approval (DOA) outside of
the service information sub-task. Therefore, we have not changed this
AD further in this regard.
Request for Clarification of Paragraph (k) of the Proposed AD
UAL requested clarification of the intent of paragraph (k) of the
proposed AD. UAL specified that the intent should be a detailed
inspection of the ``replaced'' titanium angles and not an inspection of
the four titanium angles. UAL explained that paragraph (j) of the
proposed AD states to remove the affected [cracked] titanium angle(s),
and the next inspection per paragraph (k) of the proposed AD would
apply to the replaced titanium angles, not necessarily all four
titanium angles.
We agree for the reasons provided by the commenter, and we have
revised paragraph (k) of this AD accordingly.
Request To Include Additional Data To Correct an Error in the Service
Information
UAL requested that we include information to correct an error in
the service information. UAL stated that figure A-GCAAA Sheet 02 of
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30,
2017, shows views A-A and B-B in reversed left and right direction and
that view B-B is missing one rivet location. UAL also stated that this
error makes it possible to install incorrect rivets during angle
replacement. UAL mentioned that it had contacted Airbus about this
error, and that Airbus published Technical Adaptation 80491184/005/2018
to temporarily correct the error. UAL also mentioned that Airbus plans
to revise Service Bulletin A320-53-1259 to correct this error.
We agree with the commenter's request for the reasons provided. To
ensure operators refer to the correct views and rivet locations, we
have revised this AD by referencing Airbus Technical Adaptation
80491184/005/2018, Issue 1, dated February 08, 2018, in lieu of Figure
A GCAAA--Sheet 02 of Airbus Service Bulletin A320-53-1259, Revision 03,
dated November 30, 2017, wherever it is appropriate.
[[Page 23464]]
Request To Verify the Required Service Information Prior to AD
Publication
UAL requested that we verify the latest revision of Service
Bulletin A320-53-1259 is referenced in this AD prior to final
publication. UAL indicated its preference not to request an AMOC
allowing use of a later revision of the service information immediately
after AD publication.
We agree and have confirmed that Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, is the latest version of
the service information. We have not changed this AD in this regard.
Request To Expand the Airplanes Specified in Paragraph (o) of the
Proposed AD
UAL requested that we expand the airplanes specified in paragraph
(o) of the proposed AD to include all angles that were replaced using
any service information issued prior to Airbus Service Bulletin A320-
53-1259, Revision 03, dated November 30, 2017, unless maintenance
records show that the correct rivets were previously installed. UAL
pointed out that revisions issued prior to Airbus Service Bulletin
A320-53-1259, Revision 02, dated March 24, 2016, did not specify any
procedures to install rivets to the keel beam side panel. UAL mentioned
that it could then be possible that an angle replacement done
previously using Airbus Service Bulletin A320-53-1259, dated November
6, 2012, or Airbus Service Bulletin A320-53-1259, Revision 01, dated
November 26, 2013, might have missing or incorrect rivets installed.
We disagree with the request to expand the affected airplanes
specified in paragraph (o) of this AD. As discussed previously, we have
clarified that the affected airplanes specified in paragraph (o) of
this AD are those on which a modification (replacement of affected
titanium angles) was done in accordance with Airbus Service Bulletin
A320-53-1259, Revision 02, dated March 24, 2016, and not airplanes on
which an inspection was done. Additionally, we have not received any
information from either EASA or Airbus regarding expanding the scope of
the potential unsafe condition. The new requirements in this AD are a
result of incorrect dimensions of the rivet part number provided in
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24,
2016. No such information was provided by Airbus in the previous
revisions of the service information. We have not changed this AD in
this regard.
Request for Clarification of Paragraph (o) of the Proposed AD
DAL requested that, to reduce confusion, we include clarification
in paragraph (o) of the proposed AD, that EN6081D5 rivets only need to
be installed in the fastener holes common to the titanium angle and
belly fairing wall joint. DAL mentioned that paragraph (o) of the
proposed AD provides relief for the on-wing inspection if it can be
determined no titanium angles were installed in accordance with Airbus
Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016, or if
only EN6081D5 rivets were used to install the titanium angles on that
airplane. DAL pointed out that the titanium angles are installed using
both hi-lok fasteners as well as rivets. DAL also indicated that the
hi-lok fasteners are common to the keel beam panel and the rivets are
common to the belly fairing walls.
We agree to clarify. The service information provides specific
information for a detailed inspection for the rivets on the titanium
angles and belly fairing shear wall attachments between frames (FR)40
and FR42. Additionally, as specified previously, Airbus has issued
Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February
08, 2018, as an exception to Figure A GCAAA--Sheet 02 of Airbus Service
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, which we
have included in this AD. Therefore, in paragraph (o) of this AD, where
it specifies ``or if only EN6081D5 rivets were used to install the
titanium angles on that airplane,'' the installation location for
rivets is on the titanium angles and belly fairing shear wall
attachments as identified in the service information. Since the service
information provides this information, we have not changed this AD
further regarding this issue.
Request To Use Additional Guidance for Correct Fasteners
DAL requested that we include additional guidance for accomplishing
the titanium angle replacement. DAL stated that Airbus issued Operator
Information Telex (OIT) 16-0032, Rev. 00, dated June 3, 2016, that
specified the required rivets to use for the replacement. DAL also
mentioned that Airbus issued Technical Adaptation 80170642/022/2017,
dated April 7, 2017, to Airbus Service Bulletin A320-53-1259, Revision
02, dated March 24, 2016, which specified the correct rivets for the
replacement. DAL added that the FAA could provide credit for airplanes
on which the correct rivets were installed using the OIT or technical
adaptation.
We disagree with the request. Paragraph (p)(2) of this AD refers to
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30,
2017, and Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated
February 08, 2018, which provide adequate service information for
completing the replacement required if any part number EN6081D4 series
rivet is found during any inspection required by paragraph (o) of this
AD. This AD corresponds to EASA AD 2018-0091, dated April 20, 2018,
which does not permit Airbus OIT 16-0032, Rev. 00, dated June 3, 2016,
and Airbus Technical Adaptation 80170642/022/2017, dated April 7, 2017,
as methods of compliance. We agree that those documents are not
acceptable methods of compliance with this AD because those documents
only specify the part numbers as well as the location and quantity of
the parts.
However, we do agree to clarify the statement in paragraph (o) of
this AD that describes a method of compliance for the actions required
by paragraph (o) of this AD. Paragraph (o) of this AD provides relief
for airplanes on which ``it can be determined that no titanium angles
have been installed on that airplane in accordance with the
Accomplishment Instructions of Revision 02 of Airbus Service Bulletin
A320-53-1259, or if only rivets having part number EN6081D5 have been
used to install the titanium angles.'' We have revised paragraph (o) of
this AD to clarify that the ``in accordance with the Accomplishment
Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259''
applies to the whole statement.
Clarification of Retained Effective Date for Paragraph (g) of This AD
In the introductory text of paragraph (g) of the proposed AD we
retained a compliance time that referred to the effective date of the
existing AD. However, we did not include the specific date of AD 2014-
20-04. We have revised the introductory text of paragraph (g) of this
AD to refer to the effective date of AD 2014-20-04 (November 7, 2014).
Clarification of Retained Effective Date for Paragraph (h)(3) of This
AD
In paragraph (h)(3) of the proposed AD we retained a compliance
time that referred to the effective date of the existing AD. However,
we did not include the effective date of AD 2014-20-04. We have revised
paragraph (h)(3)
[[Page 23465]]
of this AD to refer to the effective date of AD 2014-20-04 (November 7,
2014).
Conclusion
We 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. 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.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this final
rule.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017. This service information describes procedures for
repetitive inspections for cracking of the four titanium angles between
the belly fairing and the keel beam side panel, an inspection for
cracking of the open holes if any cracking is found in the titanium
angles, repair or replacement if necessary, and a detailed inspection
for and replacement of certain rivets (including a rotating probe test
for cracks in the open holes).
Airbus has also issued Technical Adaptation 80491184/005/2018,
Issue 1, dated February 08, 2018. This service information describes a
correction to Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017.
This AD also requires Airbus Service Bulletin A320-53-1014,
Revision 2, dated September 1, 1994, which the Director of the Federal
Register approved for incorporation by reference as of November 7, 2014
(79 FR 59636, October 3, 2014).
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 1,250 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
295 work[dash]hours x $85 per $1,045 $26,120................... $32,650,000.
hour = $25,075 (Retained
actions from AD 2014-20-04).
Up to 168 work[dash]hours x $85 0 Up to $14,280............. Up to $17,850,000.
per hour = Up to $14,280 (New
actions of this AD).
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacement
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:
Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
Cost per
Labor cost Parts cost \*\ product
----------------------------------------------------------------------------------------------------------------
168 work-hours x $85 per hour = $14,280....................................... $0 $14,280
----------------------------------------------------------------------------------------------------------------
* We have received no definitive data that would enable us to provide cost estimates for the on-condition parts
costs.
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 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:
[[Page 23466]]
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)
2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014), and
adding the following new AD:
2019-08-07 Airbus SAS: Amendment 39-19628; Docket No. FAA-2018-0795;
Product Identifier 2018-NM-076-AD.
(a) Effective Date
This AD is effective June 26, 2019.
(b) Affected ADs
This AD replaces AD 2014-20-04, Amendment 39-17977 (79 FR 59636,
October 3, 2014) (``AD 2014-20-04'').
(c) Applicability
This AD applies to the Airbus SAS airplanes specified in
paragraphs (c)(1), (c)(2), (c)(3), and (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 53, Fuselage.
(e) Reason
This AD was prompted by reports of cracks at the lower riveting
of the four titanium angles that connect the belly fairing to the
keel beam side panels on both sides of the fuselage. We are issuing
this AD to address cracking of the titanium angles that connect the
belly fairing to the keel beam side panels on both sides of the
fuselage, which could affect the structural integrity of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained Modification, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2014-20-04, with no changes. For Model A320-211 and -231 series
airplanes, manufacturer serial numbers 003 through 092 inclusive:
Prior to the accumulation of 12,000 total landings on the airplane,
or within 300 days after January 10, 1994 (the effective date of AD
93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)),
whichever occurs later, modify the belly fairing structure, in
accordance with the Accomplishment Instructions of an Airbus service
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this
AD. As of November 7, 2014 (the effective date of AD 2014-20-04),
use only the Airbus service bulletin specified in paragraph (g)(3)
of this AD.
(1) Airbus Industrie Service Bulletin A320-53-1014, dated June
25, 1992.
(2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1,
dated May 26, 1993.
(3) Airbus Service Bulletin A320-53-1014, Revision 2, dated
September 1, 1994.
(h) Retained Repetitive Inspection, With Updated Service Information
This paragraph restates the requirements of paragraph (h) of AD
2014-20-04, with updated service information. At the latest of the
compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3)
of this AD: Do a detailed inspection for cracking of the four
titanium angles between the belly fairing and the keel beam side
panel, in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1259, dated November 6, 2012; Airbus
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013;
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24,
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017. After the effective date of this AD, only Airbus
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017,
may be used. Where Airbus Service Bulletin A320-53-1259, Revision
03, dated November 30, 2017, specifies to refer to Figure A GCAAA--
Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018,
Issue 1, dated February 08, 2018.
(1) Before the accumulation of 30,000 total flight cycles or
60,000 total flight hours, whichever occurs first after first flight
of the airplane.
(2) Within 30,000 flight cycles or 60,000 flight hours,
whichever occurs first after modification of the airplane as
required by paragraph (g) of this AD, or after installation of new
titanium angles, provided that, prior to installation, a rototest
for cracking on the open holes has been accomplished with no crack
findings, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013;
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24,
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017. After the effective date of this AD, only Airbus
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017,
may be used. Where Airbus Service Bulletin A320-53-1259, Revision
03, dated November 30, 2017, specifies to refer to Figure A GCAAA--
Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018,
Issue 1, dated February 08, 2018.
(3) Within 3,000 flight cycles or 6,000 flight hours, whichever
occurs first after November 7, 2014 (the effective date of AD 2014-
20-04).
(i) Retained Post-Inspection Actions for No Crack Findings, With
Updated Service Information
This paragraph restates the requirements of paragraph (i) of AD
2014-20-04, with updated service information. If, during any
inspection required by paragraph (h) of this AD, there is no crack
finding: Accomplish the actions specified in either paragraph (i)(1)
or (i)(2) of this AD.
(1) Repeat the inspection required by paragraph (h) of this AD
at intervals not to exceed 5,000 flight cycles or 10,000 flight
hours, whichever occurs first.
(2) Before further flight after the inspection required by
paragraph (h) of this AD, remove all inspected titanium angles,
accomplish a rototest for cracking on the open holes and, provided
no cracks are found, install new titanium angles, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259,
Revision 01, dated November 26, 2013; or Airbus Service Bulletin
A320-53-1259, Revision 03, dated November 30, 2017. After the
effective date of this AD, only Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, may be used. Where
Airbus Service Bulletin A320-53-1259, Revision 03, dated November
30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead
use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated
February 08, 2018.
(j) Retained Post-Inspection Actions for Any Crack Findings, With
Updated Service Information
This paragraph restates the requirements of paragraph (j) of AD
2014-20-04, with updated service information. If, during any
inspection required by paragraph (h) of this AD, there is any crack
finding: Before further flight, remove the affected titanium
angle(s), accomplish a rototest for cracking on the open holes, and,
provided no cracks are found, install new titanium angles, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1259, dated November 6, 2012; Airbus Service
Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or
Airbus Service Bulletin A320-53-1259, Revision 03, dated November
30, 2017. After the effective date of this AD, only Airbus Service
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be
used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02,
instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1,
dated February 08, 2018.
(k) Retained Post-Installation Repetitive Inspections, With Updated
Service Information and Revised Compliance Language
This paragraph restates the requirements of paragraph (k) of AD
2014-20-04, with updated service information and revised compliance
language. For airplanes on which new titanium angles were installed
as specified in paragraph (i)(2) or (j) of this AD: Within 30,000
flight cycles or 60,000 flight hours, whichever occurs first after
the installation, accomplish a detailed inspection for cracking of
the replaced titanium angles between the belly fairing and the keel
beam side panel, in accordance with the Accomplishment Instructions
of Airbus
[[Page 23467]]
Service Bulletin A320-53-1259, dated November 6, 2012; Airbus
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013;
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24,
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017. After the effective date of this AD, only Airbus
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017,
may be used. Repeat the inspection thereafter at intervals not to
exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs
first. Where Airbus Service Bulletin A320-53-1259, Revision 03,
dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet
02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue
1, dated February 08, 2018.
(l) Retained Post-Inspection Actions for Any Crack Findings During
Post-Installation Inspections, With Updated Service Information
This paragraph restates the requirements of paragraph (l) of AD
2014-20-04, with updated service information. If, during any
inspection as required by paragraph (k) of this AD, there is any
crack finding: Before further flight, remove the affected titanium
angles, accomplish a rototest for cracking on the open holes, and,
provided no cracks are found, install new titanium angles, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-53-1259, dated November 6, 2012; Airbus Service
Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or
Airbus Service Bulletin A320-53-1259, Revision 03, dated November
30, 2017. After the effective date of this AD, only Airbus Service
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be
used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02,
instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1,
dated February 08, 2018.
(m) Retained Corrective Action for Rototest Crack Finding, With Updated
Contact Information
This paragraph restates the requirements of paragraph (m) of AD
2014-20-04, with updated contact information. If, during any
rototest as required by paragraph (i), (j), or (l) of this AD, any
crack is found: Before further flight, repair 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.
(n) Retained No Termination Action for Repetitive Inspections, With No
Changes
This paragraph restates the requirements of paragraph (n) of AD
2014-20-04, with no changes. Repair or replacement of parts as
specified in this AD does not terminate the repetitive inspections
required by this AD.
(o) New Requirement of This AD: Detailed Inspection for Certain Rivets
For airplanes previously modified (replacement of affected
titanium angles) using the Accomplishment Instructions of Revision
02 of Airbus Service Bulletin A320-53-1259: At the earlier of the
times specified in paragraphs (o)(1) and (o)(2) of this AD, do a
detailed inspection of the rivet installation in the belly fairing
shear walls and the titanium angles for part number EN6081D4 series
rivets in accordance with the Accomplishment Instructions of Airbus
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017.
A review of the airplane maintenance records is acceptable to comply
with the requirements of this paragraph for that airplane, provided
it can be determined that no titanium angles have been installed on
that airplane in accordance with the Accomplishment Instructions of
Revision 02 of Airbus Service Bulletin A320-53-1259, or if only
rivets having part number EN6081D5 have been used to install the
titanium angles on that airplane in accordance with the
Accomplishment Instructions of Revision 02 of Airbus Service
Bulletin A320-53-1259. Where Airbus Service Bulletin A320-53-1259,
Revision 03, dated November 30, 2017, specifies to refer to Figure A
GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/
005/2018, Issue 1, dated February 08, 2018.
(1) Within 2,000 flight cycles or 4,000 flight hours, whichever
occurs first after the effective date of this AD.
(2) Before exceeding 5,000 flight cycles or 10,000 flight hours,
whichever occurs first after accomplishment of the last inspection
specified in paragraph (h) of this AD.
(p) New Requirements of This AD: Replacement of Certain Rivets
If any part number EN6081D4 series rivet is found during any
inspection required by paragraph (o) of this AD, before further
flight, do the actions specified in paragraphs (p)(1) and (p)(2) of
this AD.
(1) Remove the part number EN6081D4 series rivets and do a
rotating probe test of the open holes for cracks, in accordance with
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017. If any crack is found
during any inspection required by this paragraph, before further
flight, obtain corrective actions approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus SAS's EASA DOA; and accomplish the corrective actions within
the compliance time specified therein. If approved by the DOA, the
approval must include the DOA-authorized signature.
(2) Replace part number EN6081D4 series rivets with part number
EN6081D5 series rivets in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1259, Revision 03,
dated November 30, 2017. Where Airbus Service Bulletin A320-53-1259,
Revision 03, dated November 30, 2017, specifies to refer to Figure A
GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/
005/2018, Issue 1, dated February 08, 2018.
(q) Service Information Exception
Where the Accomplishment Instructions of Airbus Service Bulletin
A320-53-1259, Revision 03, dated November 30, 2017, specify to
install titanium angle part numbers D5337060121200 and
D5337060121400, this AD allows the installation of titanium angle
part numbers D5337060121295 and D5337060121495, respectively.
(r) 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 (s)(2) of this AD. Information
may be emailed to: [email protected].
(i) 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.
(ii) AMOCs approved previously for AD 2014-20-04, are approved
as AMOCs for the corresponding provisions of this AD.
(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 EASA; or Airbus SAS's EASA 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.
(s) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0091, dated April 20, 2018, for related
information. This MCAI may be found in the AD docket on the internet
at https://www.regulations.gov by searching for and locating Docket
No. FAA-2018-0795.
(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; phone and
fax: 206-231-3223.
(t) 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.
[[Page 23468]]
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
June 26, 2019.
(i) Airbus Service Bulletin A320-53-1259, Revision 03, dated
November 30, 2017.
(ii) Airbus Technical Adaptation 80491184/005/2018, Issue 1,
dated February 08, 2018. The date appears only on the last page of
the document.
(4) The following service information was approved for IBR on
November 7, 2014 (79 FR 59636, October 3, 2014).
(i) Airbus Service Bulletin A320-53-1014, Revision 2, dated
September 1, 1994, including supplementary page 7A. Pages 1 through
3, 15, 19, 20, and 25 of this document are identified as Revision 2,
dated September 1, 1994; pages 4 through 8, 10, 12, 16 through 18,
and 21 through 24 are identified as Revision 1, dated May 26, 1993;
and pages 9, 11, 13, 14, and 26 are identified as the original,
dated June 25, 1992.
(ii) [Reserved]
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax:
+33 5 61 93 44 51; email: [email protected]; internet:
https://www.airbus.com.
(6) 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.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on April 10, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2019-10653 Filed 5-21-19; 8:45 am]
BILLING CODE 4910-13-P
