AD 2018-14-09

[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 [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[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.

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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 <a href="/cdn-cgi/l/email-protection#d9b8babab6acb7adf7b8b0abaeb6abadb1f4bcb8aa99b8b0abbbacaaf7bab6b4"><span class="__cf_email__" data-cfemail="83e2e0e0ecf6edf7ade2eaf1f4ecf1f7ebaee6e2f0c3e2eaf1e1f6f0ade0ecee">[email&#160;protected]</span></a>; internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
1093.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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.
    <bullet> 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.
    <bullet> 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).

BILLING CODE 4910-13-P

[[Page 34038]]

[GRAPHIC] [TIFF OMITTED] TR19JY18.002

[GRAPHIC] [TIFF OMITTED] TR19JY18.003

BILLING CODE 4910-13-C

(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: <a href="/cdn-cgi/l/email-protection#635a4e222d2e4e5252554e222e2c204e3126323626303730230502024d040c15"><span class="__cf_email__" data-cfemail="c0f9ed818e8dedf1f1f6ed818d8f83ed928591958593949380a6a1a1eea7afb6">[email&#160;protected]</span></a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> 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 <a href="/cdn-cgi/l/email-protection#6d0c0e0e02180319430c041f1a021f190540080c1e2d0c041f0f181e430e0200"><span class="__cf_email__" data-cfemail="aecfcdcdc1dbc0da80cfc7dcd9c1dcdac683cbcfddeecfc7dcccdbdd80cdc1c3">[email&#160;protected]</span></a>; internet 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    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]
BILLING CODE 4910-13-P