Airworthiness Directives; Airbus Airplanes, 34034-34039 [2018-14687]
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34034
Federal Register / Vol. 83, No. 139 / Thursday, July 19, 2018 / Rules and Regulations
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the manager of the International
Branch, send it to the attention of the person
identified in paragraph (l)(2) of this AD.
Information may be emailed to: 9-ANM-116AMOC-REQUESTS@faa.gov. Before using
any approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2017–0223R1, dated December 15, 2017, 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–2018–0166.
(2) For more information about this AD,
contact Shahram Daneshmandi, Aerospace
Engineer, International Section, Transport
Standards Branch, FAA, 2200 South 216th
St., Des Moines, WA 98198; telephone and
fax 206–231–3220.
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(m) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) ATR72 Time Limits document, Revision
15, dated May 2, 2017.
(ii) Reserved.
(3) For service information identified in
this AD, contact ATR–GIE Avions de
´
´
Transport Regional, 1, Allee Pierre Nadot,
31712 Blagnac Cedex, France; telephone +33
(0) 5 62 21 62 21; fax +33 (0) 5 62 21 67 18;
email continued.airworthiness@atraircraft.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.
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Issued in Des Moines, Washington, on July
3, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–14809 Filed 7–18–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2017–1093; Product
Identifier 2017–NM–018–AD; Amendment
39–19329; AD 2018–14–09]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Airbus Model A318 series airplanes;
Model A319 series airplanes; Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. This AD
was prompted by reports of early
cracking on certain holes of the
crossbeam splicing at certain fuselage
frames. This AD requires repetitive
inspections for cracking of the fastener
holes in certain fuselage frames, and
depending on airplane configuration,
provides an optional terminating action
to the repetitive inspections. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective August 23,
2018.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of August 23, 2018.
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS,
Rond-Point Emile Dewoitine No: 2,
31700 Blagnac Cedex, France; telephone
+33 5 61 93 36 96; fax +33 5 61 93 44
51; email 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
SUMMARY:
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for and locating Docket No. FAA–2017–
1093.
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–2017–
1093; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Office (telephone 800–647–
5527) is Docket Management Facility,
U.S. Department of Transportation,
Docket Operations, M–30, West
Building Ground Floor, Room W12–140,
1200 New Jersey Avenue SE,
Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to certain Airbus Model A318
series airplanes; Model A319 series
airplanes; Model A320–211, –212, –214,
–216, –231, –232, and –233 airplanes;
and Model A321–111, –112, –131, –211,
–212, –213, –231, and –232 airplanes.
The NPRM published in the Federal
Register on November 27, 2017 (82 FR
55955) (‘‘the NPRM’’). The NPRM was
prompted by reports of early cracking
on certain holes of the crossbeam
splicing at certain fuselage frames. The
NPRM proposed to require repetitive
inspections for cracking of the fastener
holes in certain fuselage frames, and
depending on airplane configuration,
would provide an optional terminating
action to the repetitive inspections. We
are issuing this AD to address cracking
at two upper rows of fasteners of the
crossbeam splicing at frame (FR)16 and
FR20, on both the left-hand (LH) and
right-hand (RH) sides, which can result
in reduced structural integrity of the
airplane due to the failure of structural
components.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA AD 2016–0139,
dated July 14, 2016 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
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for certain Model A318 series airplanes;
Model A319 series airplanes; Model
A320–211, –212, –214, –216, –231,
–232, and –233 airplanes; and Model
A321–111, –112, –131, –211, –212,
–213, –231, and –232 airplanes. The
MCAI states:
Following addition of a new airworthiness
limitation item (ALI) task 531110 in the
Airworthiness Limitation Section (ALS) Part
2 in the revision dated April 2012, numerous
findings have been reported of early cracks
on the four holes of the crossbeam splicing
at frame (FR)16 and FR20 on both left-hand
(LH) and right-hand (RH) sides.
This condition, if not detected and
corrected, could affect the structural integrity
of the airframe.
To allow an earlier crack detection, Airbus
decided to transfer the repetitive inspections
from ALI task 531110 to Airbus Service
Bulletin (SB) A320–53–1286, later revised,
including new recommended inspection
thresholds.
For the reasons described above, this
[EASA] AD requires repetitive special
detailed [rototest] inspections (SDI) of the
two upper rows of fasteners of the crossbeam
splicing at FR16 and FR20, on both LH and
RH sides, [installation of new fasteners on
crack-free frames, related investigative and
corrective actions,] and, depending on
aeroplane configuration, provides an optional
terminating action to the repetitive
inspections required by this [EASA] AD.
Related investigative actions include
checking the edge margins of the holes.
Corrective actions include reaming
affected crossbeams and frames and
cold working the frames. 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–2017–
1093.
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Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Requests To Revise Repair Instructions
for Repairs Done Using an Airbus
Repair Design Approval Sheet (RDAS)
American Airlines (AAL) and United
Airlines (UAL) requested that the repair
instructions in paragraph (l) of the
proposed AD be revised to remove
requirements to obtain new repair
instructions for any airplanes on which
repairs were done using the instructions
in an Airbus RDAS. AAL noted that the
original RDAS approval was given by an
EASA Design Organization Approval
(DOA), so new approval should not be
needed. Instead, AAL suggested that the
issuer of the RDASs should be required
to revise the RDASs as necessary. UAL
noted that an RDAS already defines
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repair life and inspection instructions or
limits. UAL also noted that the MCAI
does not require obtaining new repair
instructions, but instead says to
accomplish the repair instructions given
in the RDAS for repaired fastener holes.
We disagree to require the issuer of
the RDAS to revise the RDAS. An RDAS
is an Airbus document that is not
approved by the FAA, and the FAA has
no authority to require Airbus to revise
the RDAS.
We agree with the requests to remove
the requirement to obtain repair
instructions in paragraph (l) of this AD.
We have confirmed that EASA intended
the corresponding paragraph in the
MCAI to be informational, rather than a
new requirement. We have revised
paragraph (l) of this AD to note that the
information on the next inspection and
compliance time for the inspection of
repaired holes is specified in the
applicable RDAS; therefore, there is no
requirement to obtain and follow new
instructions.
Request To Supersede Certain
Inspections
UAL requested that we revise
paragraph (l) of the proposed AD to state
that previous repair instructions that
superseded ALI 531110 also terminate
the inspections required by paragraph
(g) of the proposed AD for the repaired
holes. UAL noted that they had several
RDASs that state that the inspection
requirements of the RDAS supersede
ALI 531110 for the repaired fasteners.
UAL stated that these repairs involved
enlarging the holes and fasteners,
thereby making it impossible for them to
accomplish the inspections in
accordance with Airbus Service Bulletin
A320–53–1286, Revision 01, dated
December 22, 2015.
We disagree with revising paragraph
(l) of this AD to specify terminating
action to paragraph (g) of this AD. An
operator who is unable to complete
certain requirements in this AD due to
existing repairs may request an
alternative method of compliance
(AMOC) under the provisions of
paragraph (s)(1) of this AD.
Request To Remove or Revise
Paragraph (n) of the Proposed AD
AAL requested that paragraph (n) of
the proposed AD be revised to remove
requirements to obtain new repair
instructions for any airplanes on which
repairs were done using the instructions
in an Airbus RDAS unrelated to ALI
task 531110. AAL noted that the original
RDAS approval was given by an EASA
DOA, so new approval should not be
needed. Instead, AAL suggested that the
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34035
issuer of the RDASs should be required
to revise the RDASs as necessary.
UAL requested that paragraph (n) of
the proposed AD be removed. UAL
stated that determining if a repair is
unrelated to ALI task 531110 may be
inconclusive, since the ALI task is an
inspection that may or may not be
referenced in a documented repair. UAL
added that each repair approval will
have damage tolerance considerations
regardless of how the damage was
found. UAL further noted that if a repair
unrelated to ALI task 531110 prevents
inspection or repair as specified in the
proposed AD, operators would need to
request an AMOC.
We disagree with the commenters’
requests. EASA has determined that
repairs unrelated to ALI task 531110,
which could include minor repairs
unrelated to the unsafe condition, may
not adequately address the unsafe
condition. For this reason, operators
must request new corrective actions for
such repairs, as specified in paragraph
(n) of this AD.
Requests To Revise Repair Instructions
for Airplanes on Which Certain Repairs
Were Previously Applied
UAL and AAL requested that
paragraphs (i) and (j) of the proposed
AD be revised to list specific affected
manufacturer serial numbers (MSNs). In
addition, UAL and AAL requested that
the original equipment manufacturer
(OEM) revise the Airbus RDASs to
correct any problems. AAL pointed out
that the original RDAS was approved by
an EASA DOA and stated that operators
should therefore not be required to
obtain a new approval. UAL requested
that if we do not provide revised RDASs
or a list of affected MSNs, we instead
provide a pre-defined solution for the
repair. UAL suggested that we should
provide instructions for replacing
EN6114 fasteners with EN6115
fasteners. UAL further requested that if
the repairs require case-by-case
evaluations, the repair instructions
should define the repair compliance
time, rather than having a set 24 month
compliance time, which may not work
for every configuration.
UAL also noted that the issue with
Airbus Repair Instruction R53112926
issue A or B is that it called out the
wrong fastener; EN6115 should have
been used instead of EN6114.
UAL requested that we add a
statement to paragraph (j) of this AD
stating that no additional repair
instructions are needed if a repair was
accomplished using Airbus Repair
Instruction R53112926 issue A or B and
EN6115 fasteners.
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We disagree with the commenters’
requests to revise paragraphs (i) and (j)
of this AD to list specific affected MSNs.
EASA, as the state of design authority,
and Airbus have both stated that they do
not have knowledge of prior approved
repairs; therefore we do not have a list
of affected MSNs. In addition, an RDAS
is an Airbus document that is not
approved by the FAA, and the FAA has
no authority to require Airbus to revise
the RDAS. Therefore, each existing
repair must be individually analyzed
before a new corrective action can be
provided. For this reason, we are not
able to provide a single pre-defined
solution for the repair that would
address every affected configuration. We
have determined that 24 months is an
appropriate time frame to address the
unsafe condition related to the EN6114
fasteners. An AMOC in accordance with
paragraph (s)(1) of this AD may be
requested if additional time is needed to
address the unsafe condition.
We do not agree to add a statement to
paragraphs (i) or (j) of this AD regarding
no additional repair instructions are
necessary if those repairs were applied
with the installation of EN6115
fasteners, but we do agree to clarify that
paragraphs (i) and (j) of this AD only
apply to airplanes on which Airbus
Repair Instruction R53112926 issue A or
B or any other repair involving the
installation of EN6114 fasteners was
applied. If EN6115 fasteners were
installed in the accomplishment of
Airbus Repair Instruction R53112926
issue A or B or any other repair, the
actions specified in paragraphs (i) or (j)
of this AD are not required on the
repaired airplane.
Request To Include Corrections to
Service Information
UAL requested that we update
paragraph (k) of the proposed AD to
reflect corrections to Airbus Service
Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29,
2015. UAL noted that Airbus has
released Operators Information
Transmission (OIT) 15–0097, Revision
01, dated January 7, 2016, to correct
discrepancies in the effectivity section
and existing hole diameters for certain
subtasks in Airbus Service Bulletin
A320–53–1295, including Appendixes
01 and 02, dated June 29, 2015.
We agree with the commenter’s
request for the reasons provided. We
have added paragraph (r) to this AD to
clarify the hole-diameter correction
provided in Airbus OIT 15–0097,
Revision 01, dated January 7, 2016. We
have also updated other paragraphs of
this AD that refer to Airbus Service
Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29,
2015, to include this exception. We also
acknowledge the discrepancy in the
effectivity section of Airbus Service
Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29,
2015, and the correction provided in
Airbus OIT 15–0097, Revision 01, dated
January 7, 2016. However, the
applicability of this AD does not refer to
Airbus Service Bulletin A320–53–1295,
including Appendixes 01 and 02, dated
June 29, 2015. Therefore, we have not
changed this AD in this regard.
proposed AD are at the latest revision
level. UAL noted this would eliminate
the need to request an AMOC
immediately following publication of
this AD.
We agree with the commenter’s
request. We have verified that no
revisions of the referenced service
information have been published since
we issued our proposed AD.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
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
correcting 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 AD.
Request To Verify Title of Table 1 to
Paragraphs (g) and (n) of This AD
Virgin America requested that we
review the title of table 1 to paragraphs
(g) and (n) of this AD. Virgin America
noted that the related MCAI table refers
to airplanes having not embodied any of
‘‘mod 20416 and mod 21999,’’ while the
proposed AD refers to ‘‘pre-modification
20416 or pre-modification 21999’’
airplanes. Virgin America suggested this
might be a typographical error, and
asked that it be corrected if it is in error.
We acknowledge that the wording in
the MCAI and this AD is not the same
and agree to clarify. Table 1 of the MCAI
is intended to apply to airplanes that
have not embodied any part of
modification 20416 or any part of
modification 21999. Therefore, it is
accurate to state ‘‘pre-modification
20416 or pre-modification 21999
airplanes.’’ We have not changed this
AD in this regard.
Costs of Compliance
Request To Verify Referenced Service
Information is at the Latest Revision
UAL requested that we verify the
service bulletins referenced in the
We estimate that this AD affects 928
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
Related Service Information Under
1 CFR Part 51
Airbus has issued the following
service information.
• Service Bulletin A320–53–1286,
Revision 01, dated December 22, 2015,
which describes procedures for rototest
inspections for cracking of the holes in
certain fuselage frames and crossbeams.
• Service Bulletin A320–53–1295,
including Appendixes 01 and 02, dated
June 29, 2015, which describes
procedures for modifying the airplane,
including cold working instructions in
certain fuselage frames and crossbeams.
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.
ESTIMATED COSTS
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Action
Labor cost
Inspections ......................
116 work-hours × $85 per hour = $9,860 per inspection cycle.
28 work-hours × times; $85 per hour = $2,380 ..........
Optional Modification .......
We have received no definitive data
that would enable us to provide cost
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Parts cost
Cost per product
$960
$10,820 per inspection cycle ..........
3,020
$5,400 .............................................
estimates for the on-condition actions
specified in this AD.
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Cost on U.S. operators
$10,040,960 per inspection
cycle.
Up to $5,011,200.
Authority for this Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
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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 to the Director of the System
Oversight Division.
Regulatory Findings
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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,
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2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979),
3. Will not affect intrastate aviation in
Alaska, and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–14–09 Airbus: Amendment 39–19329;
Docket No. FAA–2017–1093; Product
Identifier 2017–NM–018–AD.
(a) Effective Date
This AD is effective August 23, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–211,
–212, –214, –216, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes,
certificated in any category, all manufacturer
serial numbers, except the airplanes specified
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in paragraphs (c)(1), (c)(2), and (c)(3) of this
AD.
(1) Airplanes on which Airbus
modification 161255 has been embodied in
production.
(2) Model A319 series airplanes on which
Airbus modifications 28238, 28162, and
28342 have been concurrently embodied in
production.
(3) Model A318 series airplanes on which
Airbus modification 39195 has been
embodied in production.
(d) Subject
Air Transport Association (ATA) of
America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of early
cracking on the four holes of the crossbeam
splicing at certain fuselage frames (FR). We
are issuing this AD to detect and correct
cracking at two upper rows of fasteners of the
crossbeam splicing at FR16 and FR20, on
both the left-hand (LH) and right-hand (RH)
sides, which can result in reduced structural
integrity of the airplane due to the failure of
structural components.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Rototest Inspections
Before exceeding the threshold specified in
table 1 to paragraphs (g) and (n) of this AD,
or table 2 to paragraphs (g) and (n) of this AD,
as applicable to airplane configuration (preor post-modification 20416 or pre- or postmodification 21999): Do a special detailed
(rototest) inspection of the two upper rows of
fasteners of the crossbeam splicing at FR16
and FR20 on both LH and RH sides, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1286, Revision 01, dated December 22,
2015. Thereafter, repeat the inspection at the
intervals specified in table 1 to paragraphs (g)
and (n) of this AD, or table 2 to paragraphs
(g) and (n) of this AD, as applicable to
airplane configuration (pre- or postmodification 20416 or pre- or postmodification 21999).
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(h) Post-Inspection Actions
Depending on the results from any
inspection required by paragraph (g) of this
AD, do the actions in paragraphs (h)(1) or
(h)(2) of this AD, as applicable.
(1) If, during any inspection required by
paragraph (g) of this AD, any crack is
detected: Before further flight, do all
applicable related investigative and
corrective actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1286, Revision 01,
dated December 22, 2015; except where
Airbus Service Bulletin A320–53–1286,
Revision 01, dated December 22, 2015,
specifies to contact Airbus for appropriate
repair, and specifies that action as ‘‘RC’’
(Required for Compliance), accomplish
corrective actions before further flight in
accordance with the procedures specified in
paragraph (s)(2) of this AD. Repair of an
airplane as required by this paragraph does
not constitute terminating action for the
repetitive inspections required by paragraph
VerDate Sep<11>2014
16:04 Jul 18, 2018
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(g) of this AD for that airplane, unless
specified otherwise in the repair instructions.
(2) If, during any inspection required by
paragraph (g) of this AD, no cracks are
detected: Before further flight, do all
applicable fastener installations, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1286, Revision 01, dated December 22,
2015.
(i) Airplanes on Which Airbus Repair
Instruction R53112926 With Installation of
EN6114 Countersunk Fasteners Was Applied
on the Frame and/or Crossbeam
For airplanes on which Airbus Repair
Instruction R53112926 at issue A or B with
installation of EN6114 countersunk fasteners
was applied on the frame and/or crossbeam
at FR16 LH or RH, or at FR20 LH or RH:
Within 24 months after the effective date of
this AD, modify the repair using a method
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
PO 00000
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Sfmt 4700
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(j) Airplanes on Which a Repair With
Installation of EN6114 Countersunk
Fasteners Was Applied on the Frame and/or
Crossbeam
For airplanes on which a repair with
installation of EN6114 countersunk fasteners,
approved by the FAA, EASA, Airbus’s EASA
DOA, or an EASA DOA (other than Airbus’s
EASA DOA), was applied on the frame and/
or crossbeam at FR16 LH or RH, or at FR20
LH or RH, in the area covered by paragraph
(g) of this AD: Within 24 months after the
effective date of this AD, modify the repair
using a method approved by the Manager,
International Section, Transport Standards
Branch FAA; or EASA; or Airbus’s EASA
DOA. If approved by the DOA, the approval
must include the DOA-authorized signature.
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(k) Optional Terminating Action for
Airplanes Post-Modification 20416 or PostModification 21999
Modification of an airplane postmodification 20416 or post-modification
21999 in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29, 2015,
except as required by paragraph (r) of this
AD, constitutes terminating action for the
repetitive inspections required by paragraph
(g) of this AD for that airplane.
(l) Information on Post-Repair Actions for
Certain Airplanes
For an airplane that has been inspected per
ALI task 531110 and repaired before the
effective date of this AD using the
instructions in an Airbus Repair Design
Approval Sheet (RDAS): each applicable
RDAS contains next inspection and
compliance time for the inspection for each
repaired hole.
(m) Partial Terminating Action for Airplanes
Post-Modification 20416 or PostModification 21999
For an airplane post-modification 20416 or
post-modification 21999, modification in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1295, including Appendixes 01 and 02,
dated June 29, 2015, except as required by
paragraph (r) of this AD, for the applicable
fastener holes, where no damage or cracks
were detected (i.e., those not repaired) during
the latest inspection as required by paragraph
(g) of this AD, constitutes terminating action
for the repetitive inspections of those fastener
holes as required by paragraph (g) of this AD
for that airplane.
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(n) Actions for Airplanes With Certain
Repairs
For an airplane that has been repaired
before the effective date of this AD in the
areas described in this AD using the
instructions in an Airbus RDAS unrelated to
ALI task 531110: Before exceeding the
compliance times specified in table 1 to
paragraphs (g) and (n) of this AD or table 2
to paragraphs (g) and (n) of this AD, as
applicable, contact the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus’s EASA
DOA for corrective action instructions and
accomplish those instructions accordingly. If
approved by the DOA, the approval must
include the DOA-authorized signature.
Accomplishment of corrective action(s) on an
airplane, as required by this paragraph, does
not constitute terminating action for the
repetitive inspections required by paragraph
(g) of this AD for that airplane, as applicable,
unless specified otherwise in the
instructions.
(o) Terminating Action for ALI Tasks
(1) Accomplishment of an inspection as
required by paragraph (g) of this AD or
instructions as required by paragraph (l) of
this AD, as applicable, constitutes
terminating action for the inspection
requirements of ALI task 531110, for that
airplane.
VerDate Sep<11>2014
16:04 Jul 18, 2018
Jkt 244001
(2) Modification of the two upper rows of
fasteners of the crossbeam splicing at FR16
and FR20 on both LH and RH sides of an
airplane, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29, 2015,
except as required by paragraph (r) of this
AD, as specified in paragraphs (k) and (m) of
this AD, constitutes terminating action for
the inspection requirements of ALI task
531110, for those holes for that airplane.
(p) No Reporting Requirement
Although Airbus Service Bulletin A320–
53–1286, Revision 01, dated December 22,
2015, specifies to submit certain information
to the manufacturer, and specifies that action
as ‘‘RC’’ (Required for Compliance), this AD
does not include that requirement.
(q) Credit for Previous Actions
This paragraph provides credit for actions
required by paragraph (g) and (h) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–53–1286, dated June 29, 2015.
(r) Service Information Exceptions
Where Subtasks 531295–960–001–001 and
532195–960–002–001 of Airbus Service
Bulletin A320–53–1295, including
Appendixes 01 and 02, dated June 29, 2015,
refer to actions when an existing hole
diameter is ‘‘more than or equal to the
minimum starting hole diameter,’’ this AD
requires applicable actions in cases where
the hole diameter is ‘‘more than or equal to
the maximum starting hole diameter.’’
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, FAA,
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Section, send it
to the attention of the person identified in
paragraph (t)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain 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’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Required for Compliance (RC): Except
as required by paragraphs (h)(1) and (p) of
this AD: 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
PO 00000
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34039
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.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2016–0139, dated July 14, 2016, 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–2017–1093.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–53–1286,
Revision 01, dated December 22, 2015.
(ii) Airbus Service Bulletin A320–53–1295,
including Appendixes 01 and 02, dated June
29, 2015.
(3) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on June
29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2018–14687 Filed 7–18–18; 8:45 am]
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Agencies
[Federal Register Volume 83, Number 139 (Thursday, July 19, 2018)]
[Rules and Regulations]
[Pages 34034-34039]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-14687]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2017-1093; Product Identifier 2017-NM-018-AD; Amendment
39-19329; AD 2018-14-09]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for certain
Airbus Model A318 series airplanes; Model A319 series airplanes; Model
A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Model
A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. This
AD was prompted by reports of early cracking on certain holes of the
crossbeam splicing at certain fuselage frames. This AD requires
repetitive inspections for cracking of the fastener holes in certain
fuselage frames, and depending on airplane configuration, provides an
optional terminating action to the repetitive inspections. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective August 23, 2018.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of August 23,
2018.
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email [email protected]; internet
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-2017-
1093.
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-2017-
1093; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The street address for the Docket Office (telephone
800-647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to certain Airbus Model A318
series airplanes; Model A319 series airplanes; Model A320-211, -212, -
214, -216, -231, -232, and -233 airplanes; and Model A321-111, -112, -
131, -211, -212, -213, -231, and -232 airplanes. The NPRM published in
the Federal Register on November 27, 2017 (82 FR 55955) (``the NPRM'').
The NPRM was prompted by reports of early cracking on certain holes of
the crossbeam splicing at certain fuselage frames. The NPRM proposed to
require repetitive inspections for cracking of the fastener holes in
certain fuselage frames, and depending on airplane configuration, would
provide an optional terminating action to the repetitive inspections.
We are issuing this AD to address cracking at two upper rows of
fasteners of the crossbeam splicing at frame (FR)16 and FR20, on both
the left-hand (LH) and right-hand (RH) sides, which can result in
reduced structural integrity of the airplane due to the failure of
structural components.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA AD
2016-0139, dated July 14, 2016 (referred to after this as the Mandatory
Continuing Airworthiness Information, or ``the MCAI''), to correct an
unsafe condition
[[Page 34035]]
for certain Model A318 series airplanes; Model A319 series airplanes;
Model A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
The MCAI states:
Following addition of a new airworthiness limitation item (ALI)
task 531110 in the Airworthiness Limitation Section (ALS) Part 2 in
the revision dated April 2012, numerous findings have been reported
of early cracks on the four holes of the crossbeam splicing at frame
(FR)16 and FR20 on both left-hand (LH) and right-hand (RH) sides.
This condition, if not detected and corrected, could affect the
structural integrity of the airframe.
To allow an earlier crack detection, Airbus decided to transfer
the repetitive inspections from ALI task 531110 to Airbus Service
Bulletin (SB) A320-53-1286, later revised, including new recommended
inspection thresholds.
For the reasons described above, this [EASA] AD requires
repetitive special detailed [rototest] inspections (SDI) of the two
upper rows of fasteners of the crossbeam splicing at FR16 and FR20,
on both LH and RH sides, [installation of new fasteners on crack-
free frames, related investigative and corrective actions,] and,
depending on aeroplane configuration, provides an optional
terminating action to the repetitive inspections required by this
[EASA] AD.
Related investigative actions include checking the edge margins of
the holes. Corrective actions include reaming affected crossbeams and
frames and cold working the frames. 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-2017-1093.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Requests To Revise Repair Instructions for Repairs Done Using an Airbus
Repair Design Approval Sheet (RDAS)
American Airlines (AAL) and United Airlines (UAL) requested that
the repair instructions in paragraph (l) of the proposed AD be revised
to remove requirements to obtain new repair instructions for any
airplanes on which repairs were done using the instructions in an
Airbus RDAS. AAL noted that the original RDAS approval was given by an
EASA Design Organization Approval (DOA), so new approval should not be
needed. Instead, AAL suggested that the issuer of the RDASs should be
required to revise the RDASs as necessary. UAL noted that an RDAS
already defines repair life and inspection instructions or limits. UAL
also noted that the MCAI does not require obtaining new repair
instructions, but instead says to accomplish the repair instructions
given in the RDAS for repaired fastener holes.
We disagree to require the issuer of the RDAS to revise the RDAS.
An RDAS is an Airbus document that is not approved by the FAA, and the
FAA has no authority to require Airbus to revise the RDAS.
We agree with the requests to remove the requirement to obtain
repair instructions in paragraph (l) of this AD. We have confirmed that
EASA intended the corresponding paragraph in the MCAI to be
informational, rather than a new requirement. We have revised paragraph
(l) of this AD to note that the information on the next inspection and
compliance time for the inspection of repaired holes is specified in
the applicable RDAS; therefore, there is no requirement to obtain and
follow new instructions.
Request To Supersede Certain Inspections
UAL requested that we revise paragraph (l) of the proposed AD to
state that previous repair instructions that superseded ALI 531110 also
terminate the inspections required by paragraph (g) of the proposed AD
for the repaired holes. UAL noted that they had several RDASs that
state that the inspection requirements of the RDAS supersede ALI 531110
for the repaired fasteners. UAL stated that these repairs involved
enlarging the holes and fasteners, thereby making it impossible for
them to accomplish the inspections in accordance with Airbus Service
Bulletin A320-53-1286, Revision 01, dated December 22, 2015.
We disagree with revising paragraph (l) of this AD to specify
terminating action to paragraph (g) of this AD. An operator who is
unable to complete certain requirements in this AD due to existing
repairs may request an alternative method of compliance (AMOC) under
the provisions of paragraph (s)(1) of this AD.
Request To Remove or Revise Paragraph (n) of the Proposed AD
AAL requested that paragraph (n) of the proposed AD be revised to
remove requirements to obtain new repair instructions for any airplanes
on which repairs were done using the instructions in an Airbus RDAS
unrelated to ALI task 531110. AAL noted that the original RDAS approval
was given by an EASA DOA, so new approval should not be needed.
Instead, AAL suggested that the issuer of the RDASs should be required
to revise the RDASs as necessary.
UAL requested that paragraph (n) of the proposed AD be removed. UAL
stated that determining if a repair is unrelated to ALI task 531110 may
be inconclusive, since the ALI task is an inspection that may or may
not be referenced in a documented repair. UAL added that each repair
approval will have damage tolerance considerations regardless of how
the damage was found. UAL further noted that if a repair unrelated to
ALI task 531110 prevents inspection or repair as specified in the
proposed AD, operators would need to request an AMOC.
We disagree with the commenters' requests. EASA has determined that
repairs unrelated to ALI task 531110, which could include minor repairs
unrelated to the unsafe condition, may not adequately address the
unsafe condition. For this reason, operators must request new
corrective actions for such repairs, as specified in paragraph (n) of
this AD.
Requests To Revise Repair Instructions for Airplanes on Which Certain
Repairs Were Previously Applied
UAL and AAL requested that paragraphs (i) and (j) of the proposed
AD be revised to list specific affected manufacturer serial numbers
(MSNs). In addition, UAL and AAL requested that the original equipment
manufacturer (OEM) revise the Airbus RDASs to correct any problems. AAL
pointed out that the original RDAS was approved by an EASA DOA and
stated that operators should therefore not be required to obtain a new
approval. UAL requested that if we do not provide revised RDASs or a
list of affected MSNs, we instead provide a pre-defined solution for
the repair. UAL suggested that we should provide instructions for
replacing EN6114 fasteners with EN6115 fasteners. UAL further requested
that if the repairs require case-by-case evaluations, the repair
instructions should define the repair compliance time, rather than
having a set 24 month compliance time, which may not work for every
configuration.
UAL also noted that the issue with Airbus Repair Instruction
R53112926 issue A or B is that it called out the wrong fastener; EN6115
should have been used instead of EN6114.
UAL requested that we add a statement to paragraph (j) of this AD
stating that no additional repair instructions are needed if a repair
was accomplished using Airbus Repair Instruction R53112926 issue A or B
and EN6115 fasteners.
[[Page 34036]]
We disagree with the commenters' requests to revise paragraphs (i)
and (j) of this AD to list specific affected MSNs. EASA, as the state
of design authority, and Airbus have both stated that they do not have
knowledge of prior approved repairs; therefore we do not have a list of
affected MSNs. In addition, an RDAS is an Airbus document that is not
approved by the FAA, and the FAA has no authority to require Airbus to
revise the RDAS. Therefore, each existing repair must be individually
analyzed before a new corrective action can be provided. For this
reason, we are not able to provide a single pre-defined solution for
the repair that would address every affected configuration. We have
determined that 24 months is an appropriate time frame to address the
unsafe condition related to the EN6114 fasteners. An AMOC in accordance
with paragraph (s)(1) of this AD may be requested if additional time is
needed to address the unsafe condition.
We do not agree to add a statement to paragraphs (i) or (j) of this
AD regarding no additional repair instructions are necessary if those
repairs were applied with the installation of EN6115 fasteners, but we
do agree to clarify that paragraphs (i) and (j) of this AD only apply
to airplanes on which Airbus Repair Instruction R53112926 issue A or B
or any other repair involving the installation of EN6114 fasteners was
applied. If EN6115 fasteners were installed in the accomplishment of
Airbus Repair Instruction R53112926 issue A or B or any other repair,
the actions specified in paragraphs (i) or (j) of this AD are not
required on the repaired airplane.
Request To Include Corrections to Service Information
UAL requested that we update paragraph (k) of the proposed AD to
reflect corrections to Airbus Service Bulletin A320-53-1295, including
Appendixes 01 and 02, dated June 29, 2015. UAL noted that Airbus has
released Operators Information Transmission (OIT) 15-0097, Revision 01,
dated January 7, 2016, to correct discrepancies in the effectivity
section and existing hole diameters for certain subtasks in Airbus
Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated
June 29, 2015.
We agree with the commenter's request for the reasons provided. We
have added paragraph (r) to this AD to clarify the hole-diameter
correction provided in Airbus OIT 15-0097, Revision 01, dated January
7, 2016. We have also updated other paragraphs of this AD that refer to
Airbus Service Bulletin A320-53-1295, including Appendixes 01 and 02,
dated June 29, 2015, to include this exception. We also acknowledge the
discrepancy in the effectivity section of Airbus Service Bulletin A320-
53-1295, including Appendixes 01 and 02, dated June 29, 2015, and the
correction provided in Airbus OIT 15-0097, Revision 01, dated January
7, 2016. However, the applicability of this AD does not refer to Airbus
Service Bulletin A320-53-1295, including Appendixes 01 and 02, dated
June 29, 2015. Therefore, we have not changed this AD in this regard.
Request To Verify Title of Table 1 to Paragraphs (g) and (n) of This AD
Virgin America requested that we review the title of table 1 to
paragraphs (g) and (n) of this AD. Virgin America noted that the
related MCAI table refers to airplanes having not embodied any of ``mod
20416 and mod 21999,'' while the proposed AD refers to ``pre-
modification 20416 or pre-modification 21999'' airplanes. Virgin
America suggested this might be a typographical error, and asked that
it be corrected if it is in error.
We acknowledge that the wording in the MCAI and this AD is not the
same and agree to clarify. Table 1 of the MCAI is intended to apply to
airplanes that have not embodied any part of modification 20416 or any
part of modification 21999. Therefore, it is accurate to state ``pre-
modification 20416 or pre-modification 21999 airplanes.'' We have not
changed this AD in this regard.
Request To Verify Referenced Service Information is at the Latest
Revision
UAL requested that we verify the service bulletins referenced in
the proposed AD are at the latest revision level. UAL noted this would
eliminate the need to request an AMOC immediately following publication
of this AD.
We agree with the commenter's request. We have verified that no
revisions of the referenced service information have been published
since we issued our proposed AD.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD 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 correcting 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 AD.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Service Bulletin A320-53-1286, Revision 01, dated December
22, 2015, which describes procedures for rototest inspections for
cracking of the holes in certain fuselage frames and crossbeams.
Service Bulletin A320-53-1295, including Appendixes 01 and
02, dated June 29, 2015, which describes procedures for modifying the
airplane, including cold working instructions in certain fuselage
frames and crossbeams.
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 928 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections..................... 116 work-hours x $85 $960 $10,820 per $10,040,960 per
per hour = $9,860 inspection cycle. inspection cycle.
per inspection cycle.
Optional Modification........... 28 work-hours x 3,020 $5,400.............. Up to $5,011,200.
times; $85 per hour
= $2,380.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition actions specified in this AD.
Authority for this Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue
[[Page 34037]]
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 to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866,
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979),
3. Will not affect intrastate aviation in Alaska, and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-14-09 Airbus: Amendment 39-19329; Docket No. FAA-2017-1093;
Product Identifier 2017-NM-018-AD.
(a) Effective Date
This AD is effective August 23, 2018.
(b) Affected ADs
None.
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-211, -212, -214, -216, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes, certificated in any category, all
manufacturer serial numbers, except the airplanes specified in
paragraphs (c)(1), (c)(2), and (c)(3) of this AD.
(1) Airplanes on which Airbus modification 161255 has been
embodied in production.
(2) Model A319 series airplanes on which Airbus modifications
28238, 28162, and 28342 have been concurrently embodied in
production.
(3) Model A318 series airplanes on which Airbus modification
39195 has been embodied in production.
(d) Subject
Air Transport Association (ATA) of America Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of early cracking on the four
holes of the crossbeam splicing at certain fuselage frames (FR). We
are issuing this AD to detect and correct cracking at two upper rows
of fasteners of the crossbeam splicing at FR16 and FR20, on both the
left-hand (LH) and right-hand (RH) sides, which can result in
reduced structural integrity of the airplane due to the failure of
structural components.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Rototest Inspections
Before exceeding the threshold specified in table 1 to
paragraphs (g) and (n) of this AD, or table 2 to paragraphs (g) and
(n) of this AD, as applicable to airplane configuration (pre- or
post-modification 20416 or pre- or post-modification 21999): Do a
special detailed (rototest) inspection of the two upper rows of
fasteners of the crossbeam splicing at FR16 and FR20 on both LH and
RH sides, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1286, Revision 01, dated December
22, 2015. Thereafter, repeat the inspection at the intervals
specified in table 1 to paragraphs (g) and (n) of this AD, or table
2 to paragraphs (g) and (n) of this AD, as applicable to airplane
configuration (pre- or post-modification 20416 or pre- or post-
modification 21999).
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(h) Post-Inspection Actions
Depending on the results from any inspection required by
paragraph (g) of this AD, do the actions in paragraphs (h)(1) or
(h)(2) of this AD, as applicable.
(1) If, during any inspection required by paragraph (g) of this
AD, any crack is detected: Before further flight, do all applicable
related investigative and corrective actions in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1286,
Revision 01, dated December 22, 2015; except where Airbus Service
Bulletin A320-53-1286, Revision 01, dated December 22, 2015,
specifies to contact Airbus for appropriate repair, and specifies
that action as ``RC'' (Required for Compliance), accomplish
corrective actions before further flight in accordance with the
procedures specified in paragraph (s)(2) of this AD. Repair of an
airplane as required by this paragraph does not constitute
terminating action for the repetitive inspections required by
paragraph (g) of this AD for that airplane, unless specified
otherwise in the repair instructions.
(2) If, during any inspection required by paragraph (g) of this
AD, no cracks are detected: Before further flight, do all applicable
fastener installations, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1286, Revision 01,
dated December 22, 2015.
(i) Airplanes on Which Airbus Repair Instruction R53112926 With
Installation of EN6114 Countersunk Fasteners Was Applied on the Frame
and/or Crossbeam
For airplanes on which Airbus Repair Instruction R53112926 at
issue A or B with installation of EN6114 countersunk fasteners was
applied on the frame and/or crossbeam at FR16 LH or RH, or at FR20
LH or RH: Within 24 months after the effective date of this AD,
modify the repair using a method approved by the Manager,
International Section, Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(j) Airplanes on Which a Repair With Installation of EN6114 Countersunk
Fasteners Was Applied on the Frame and/or Crossbeam
For airplanes on which a repair with installation of EN6114
countersunk fasteners, approved by the FAA, EASA, Airbus's EASA DOA,
or an EASA DOA (other than Airbus's EASA DOA), was applied on the
frame and/or crossbeam at FR16 LH or RH, or at FR20 LH or RH, in the
area covered by paragraph (g) of this AD: Within 24 months after the
effective date of this AD, modify the repair using a method approved
by the Manager, International Section, Transport Standards Branch
FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the
approval must include the DOA-authorized signature.
[[Page 34039]]
(k) Optional Terminating Action for Airplanes Post-Modification 20416
or Post-Modification 21999
Modification of an airplane post-modification 20416 or post-
modification 21999 in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1295, including
Appendixes 01 and 02, dated June 29, 2015, except as required by
paragraph (r) of this AD, constitutes terminating action for the
repetitive inspections required by paragraph (g) of this AD for that
airplane.
(l) Information on Post-Repair Actions for Certain Airplanes
For an airplane that has been inspected per ALI task 531110 and
repaired before the effective date of this AD using the instructions
in an Airbus Repair Design Approval Sheet (RDAS): each applicable
RDAS contains next inspection and compliance time for the inspection
for each repaired hole.
(m) Partial Terminating Action for Airplanes Post-Modification 20416 or
Post-Modification 21999
For an airplane post-modification 20416 or post-modification
21999, modification in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1295, including
Appendixes 01 and 02, dated June 29, 2015, except as required by
paragraph (r) of this AD, for the applicable fastener holes, where
no damage or cracks were detected (i.e., those not repaired) during
the latest inspection as required by paragraph (g) of this AD,
constitutes terminating action for the repetitive inspections of
those fastener holes as required by paragraph (g) of this AD for
that airplane.
(n) Actions for Airplanes With Certain Repairs
For an airplane that has been repaired before the effective date
of this AD in the areas described in this AD using the instructions
in an Airbus RDAS unrelated to ALI task 531110: Before exceeding the
compliance times specified in table 1 to paragraphs (g) and (n) of
this AD or table 2 to paragraphs (g) and (n) of this AD, as
applicable, contact the Manager, International Section, Transport
Standards Branch, FAA; or EASA; or Airbus's EASA DOA for corrective
action instructions and accomplish those instructions accordingly.
If approved by the DOA, the approval must include the DOA-authorized
signature. Accomplishment of corrective action(s) on an airplane, as
required by this paragraph, does not constitute terminating action
for the repetitive inspections required by paragraph (g) of this AD
for that airplane, as applicable, unless specified otherwise in the
instructions.
(o) Terminating Action for ALI Tasks
(1) Accomplishment of an inspection as required by paragraph (g)
of this AD or instructions as required by paragraph (l) of this AD,
as applicable, constitutes terminating action for the inspection
requirements of ALI task 531110, for that airplane.
(2) Modification of the two upper rows of fasteners of the
crossbeam splicing at FR16 and FR20 on both LH and RH sides of an
airplane, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-53-1295, including Appendixes 01 and
02, dated June 29, 2015, except as required by paragraph (r) of this
AD, as specified in paragraphs (k) and (m) of this AD, constitutes
terminating action for the inspection requirements of ALI task
531110, for those holes for that airplane.
(p) No Reporting Requirement
Although Airbus Service Bulletin A320-53-1286, Revision 01,
dated December 22, 2015, specifies to submit certain information to
the manufacturer, and specifies that action as ``RC'' (Required for
Compliance), this AD does not include that requirement.
(q) Credit for Previous Actions
This paragraph provides credit for actions required by paragraph
(g) and (h) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-53-
1286, dated June 29, 2015.
(r) Service Information Exceptions
Where Subtasks 531295-960-001-001 and 532195-960-002-001 of
Airbus Service Bulletin A320-53-1295, including Appendixes 01 and
02, dated June 29, 2015, refer to actions when an existing hole
diameter is ``more than or equal to the minimum starting hole
diameter,'' this AD requires applicable actions in cases where the
hole diameter is ``more than or equal to the maximum starting hole
diameter.''
(s) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, FAA, has the
authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Section, send it to the attention of
the person identified in paragraph (t)(2) of this AD. Information
may be emailed to: [email protected]. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office.
(2) Contacting the Manufacturer: 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's EASA
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
(3) Required for Compliance (RC): Except as required by
paragraphs (h)(1) and (p) of this AD: 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.
(t) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2016-0139, dated July 14, 2016, 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-2017-1093.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-53-1286, Revision 01, dated
December 22, 2015.
(ii) Airbus Service Bulletin A320-53-1295, including Appendixes
01 and 02, dated June 29, 2015.
(3) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email [email protected]; internet
https://www.airbus.com.
(4) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on June 29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-14687 Filed 7-18-18; 8:45 am]
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