AD 2019-08-07

[Federal Register Volume 84, Number 99 (Wednesday, May 22, 2019)]
[Rules and Regulations]
[Pages 23461-23468]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2019-10653]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD; Amendment 
39-19628; AD 2019-08-07]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2014-20-04, 
which applied to all Airbus SAS Model A318 and A319 series airplanes; 
Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and -233 
airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, -213, 
-231, and -232 airplanes. AD 2014-20-04 required repetitive inspections 
of the titanium angles between the belly fairing and the keel beam side 
panel, an inspection of the open holes of cracked titanium angles, and 
corrective action if necessary. This AD continues to require those 
actions, adds Model A320-216 airplanes, and requires a detailed 
inspection for, and replacement of, certain rivets, and corrective 
actions if necessary. This AD was prompted by reports of cracks at the 
lower riveting of the four titanium angles that connect the belly 
fairing to the keel beam side

[[Page 23462]]

panels. We are issuing this AD to address the unsafe condition on these 
products.

DATES: This AD is effective June 26, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 26, 
2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
November 7, 2014 (79 FR 59636, October 3, 2014).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; 
fax: +33 5 61 93 44 51; email: <a href="/cdn-cgi/l/email-protection#214042424e544f550f404853564e5355490c444052614048534354520f424e4c"><span class="__cf_email__" data-cfemail="670604040812091349060e15100815130f4a02061427060e150512144904080a">[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-2018-0795.

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-2018-
0795; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this final rule, the regulatory evaluation, any comments received, and 
other information. The address for Docket Operations (phone: 800-647-
5527) is U.S. Department of Transportation, Docket Operations, M-30, 
West Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE, 
Washington, DC 20590.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; phone and fax: 206-231-3223.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-20-04, Amendment 39-17977 (79 FR 59636, 
October 3, 2014) (``AD 2014-20-04''). AD 2014-20-04 applied to all 
Airbus SAS Model A318 series airplanes; Airbus SAS Model A319 series 
airplanes; Airbus SAS Model A320-111, -211, -212, -214, -231, -232, and 
-233 airplanes; and Airbus SAS Model A321-111, -112, -131, -211, -212, 
-213, -231, and -232 airplanes. The NPRM published in the Federal 
Register on September 17, 2018 (83 FR 46905). The NPRM was prompted by 
our determination that additional work is necessary for certain 
airplanes. The NPRM proposed to continue to require repetitive 
inspections for cracking of the four titanium angles between the belly 
fairing and the keel beam side panel, an inspection for cracking of the 
open holes if any cracking is found in the titanium angles, and repair 
or replacement if necessary. The NPRM also proposed to revise the 
applicability by adding Model A320-216 airplanes. The NPRM also 
proposed additional work, including a detailed inspection for, and 
replacement of, certain rivets (including a rotating probe test for 
cracks in the open holes), and corrective actions if necessary. We are 
issuing this AD to address cracking at the lower riveting of the four 
titanium angles that connect the belly fairing to the keel beam side 
panels on both sides of the fuselage, which could affect the structural 
integrity of the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0091, dated April 20, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A318 series 
airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model 
A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Airbus 
SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    During the fatigue test campaign of the A320 family type design, 
cracks were found at the lower riveting of the four titanium angles 
which connect the belly fairing to the keel beam side panels between 
frames FR40 and FR42, on both sides of the fuselage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1014, and DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 92-
201-030 [which corresponds to FAA AD 94-12-03, Amendment 39-8930 (59 
FR 28763, June 3, 1994) (``AD 94-12-03'')] to require reinforcement 
of the belly fairing structure.
    Following new investigation which showed that these measures 
addressed only part of the unsafe condition, Airbus published SB 
A320-53-1259 and EASA issued AD 2013-0122 [which corresponds to FAA 
AD 2014-20-04], retaining the requirements of DGAC France AD 92-201-
030, which was superseded, and requiring repetitive detailed 
inspections (DET) of the affected titanium angles and, depending on 
findings, repair or replacement of parts.
    After that [EASA] AD was issued, Airbus published Revision 
(Rev.) 01 and Rev. 02 of SB A320-53-1259. [Airbus SB A320-53-1259] 
Rev. 02 provided incorrect instructions to use Part Number (P/N) 
EN6081D4 rivets for the titanium angles installation, instead of P/N 
EN6081D5 rivets. Consequently, Airbus SB A320-53-1259 was updated 
(now at Rev. 03) including reference to the proper rivets.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0122, which is superseded, and requires 
additional work [a detailed inspection for and replacement of 
certain rivets, and applicable corrective actions] for aeroplanes on 
which Airbus SB A320-53-1259 at Rev. 02 was embodied.

    You may examine the MCAI in the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2018-
0795.

Comments

    We gave the public the opportunity to participate in developing 
this final rule. The following presents the comments received on the 
NPRM and the FAA's response to each comment.

Request To Withdraw the NPRM

    Delta Air Lines (DAL) requested that we re-issue the NPRM using the 
method where the FAA AD would mandate the EASA AD for compliance (i.e., 
the ``incorporate by reference (IBR) the MCAI'' method). DAL pointed 
out this method would simplify the understanding of the NPRM and reduce 
the number of conflicts between the EASA AD and the NPRM.
    We acknowledge the commenter's request to use the ``IBR the MCAI'' 
method. Using the ``IBR the MCAI'' method simplifies FAA ADs and 
facilitates a simpler AD process. However, we disagree with the request 
to re-issue the NPRM using this method, as it would require an 
additional public comment period and unnecessarily delay issuance of 
this final rule, which is necessary to address the identified unsafe 
condition. However, based on positive feedback from operators, we are 
expanding the use of the ``IBR the MCAI'' method, and additional NPRMs 
and ADs are currently being drafted using this method.

Request To Use Previously Existing Alternative Method of Compliance 
(AMOC) for Compliance With This AD

    DAL requested that we allow the use of AMOC ANM-116-15-018 for 
compliance with all corresponding

[[Page 23463]]

provisions of the proposed AD. DAL also requested that if the FAA 
disagrees to include the use of the AMOC as requested, that we include 
details in the NPRM for addressing the airplanes already inspected and 
modified using the AMOC and Airbus Service Bulletin A320-53-1259, 
Revision 01, dated November 26, 2013. DAL mentioned that several 
airplanes from the DAL fleet were inspected and modified using the AMOC 
and Airbus Service Bulletin A320-53-1259, Revision 01, dated November 
26, 2013. DAL also pointed out that the NPRM does not provide credit 
for work performed using the AMOC and Airbus Service Bulletin A320-53-
1259, Revision 01, dated November 26, 2013.
    We agree to allow the use of the AMOC identified by the commenter, 
as well as all other AMOCs to AD 2014-20-04, and we have added 
paragraph (r)(1)(ii) to this AD accordingly.

Request To Use All Revisions of the Service Information for Inspection 
Compliance in Paragraph (h) of the Proposed AD

    DAL requested that we include Airbus Service Bulletin A320-53-1259, 
Revision 01, dated November 26, 2013, and Airbus Service Bulletin A320-
53-1259, Revision 02, dated March 24, 2016, as service information for 
the inspection requirements of the proposed AD. DAL pointed out that 
the removal and installation of the titanium angles is the main concern 
in limiting the use of Airbus Service Bulletin A320-53-1259, Revision 
02, dated March 24, 2016, but that the inspection requirements contain 
no errors. DAL also indicated concurrence with the requirement to use 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 
2017, after the effective date of the final rule.
    We agree for the reasons provided by the commenter and have revised 
the introductory text of paragraph (h) and paragraphs (h)(2) and (k) of 
this AD accordingly. However, we have only revised paragraphs (i)(2), 
(j), and (l) of this AD to include Airbus Service Bulletin A320-53-
1259, Revision 01, dated November 26, 2013, because those paragraphs 
include installation requirements and Revision 02 of Airbus Service 
Bulletin A320-53-1259 is not acceptable service information for doing 
those installations.

Request To Use Alternative Part Number Titanium Angles

    United Air Lines (UAL) requested that we allow titanium angle part 
numbers D5337060121295 and D5337060121495 to be installed instead of 
part numbers D5337060121200 and D5337060121400, respectively. UAL 
stated that titanium angle part numbers D5337060121200 and 
D5337060121400 as specified by Airbus Service Bulletin A320-53-1259, 
Revision 03, dated November 30, 2017, are not procurable. UAL mentioned 
that Airbus indicated to UAL that titanium angle part numbers 
D5337060121295 and D5337060121495 are acceptable for installation for 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 
2017.
    We agree with the commenter for the reasons provided. We have added 
paragraph (q) to this AD to allow the installation of titanium angle 
part numbers D5337060121295 and D5337060121495. We have redesignated 
subsequent paragraphs accordingly.

Request To Revise the Affected Airplanes for Paragraph (o) of the 
Proposed AD

    DAL and UAL requested that we revise the affected airplanes for 
paragraph (o) of the proposed AD. UAL requested that we clarify the 
service information reference for description of the affected airplanes 
in paragraph (o) of the proposed AD. DAL and UAL pointed out that the 
MCAI specifies Revision 02 of Airbus Service Bulletin A320-23-1259 for 
the action specified in paragraph (o) of the proposed AD and that 
paragraph (o) of the proposed AD specifies Airbus Service Bulletin 
A320-53-1259, dated November 6, 2012, for identifying affected 
airplanes.
    In addition, DAL requested that we revise paragraph (o) of the 
proposed AD to apply only to airplanes which had titanium angles 
removed and replaced in accordance with sub-task 531259-203-001 of 
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 
2016. DAL pointed out that paragraph (o) of the proposed AD specified 
airplanes which were inspected using Airbus Service Bulletin A320-53-
1259, dated November 6, 2012. DAL mentioned that the unsafe condition 
was introduced in Airbus Service Bulletin A320-53-1259, Revision 02, 
dated March 24, 2016, and that there are no airworthiness concerns with 
the inspections (only replacements) accomplished under any revision of 
the service information.
    We agree that paragraph (o) of this AD should refer to Airbus 
Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016, to 
identify the affected airplanes as specified in the MCAI, and we have 
revised paragraph (o) of this AD accordingly.
    We also agree with the request to limit the affected airplanes to 
those that had titanium angles replaced in accordance with sub-task 
531259-203-001 of Airbus Service Bulletin A320-53-1259, Revision 02, 
dated March 24, 2016. However, we have determined that the phrase 
``modified (replacement of affected titanium angles),'' which matches 
the intent of the language in the MCAI, is more appropriate instead of 
listing specific sub-tasks for replacement. Operators may have 
installed these rivets in accordance with instructions approved by 
Airbus SAS under EASA's Design Organization Approval (DOA) outside of 
the service information sub-task. Therefore, we have not changed this 
AD further in this regard.

Request for Clarification of Paragraph (k) of the Proposed AD

    UAL requested clarification of the intent of paragraph (k) of the 
proposed AD. UAL specified that the intent should be a detailed 
inspection of the ``replaced'' titanium angles and not an inspection of 
the four titanium angles. UAL explained that paragraph (j) of the 
proposed AD states to remove the affected [cracked] titanium angle(s), 
and the next inspection per paragraph (k) of the proposed AD would 
apply to the replaced titanium angles, not necessarily all four 
titanium angles.
    We agree for the reasons provided by the commenter, and we have 
revised paragraph (k) of this AD accordingly.

Request To Include Additional Data To Correct an Error in the Service 
Information

    UAL requested that we include information to correct an error in 
the service information. UAL stated that figure A-GCAAA Sheet 02 of 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 
2017, shows views A-A and B-B in reversed left and right direction and 
that view B-B is missing one rivet location. UAL also stated that this 
error makes it possible to install incorrect rivets during angle 
replacement. UAL mentioned that it had contacted Airbus about this 
error, and that Airbus published Technical Adaptation 80491184/005/2018 
to temporarily correct the error. UAL also mentioned that Airbus plans 
to revise Service Bulletin A320-53-1259 to correct this error.
    We agree with the commenter's request for the reasons provided. To 
ensure operators refer to the correct views and rivet locations, we 
have revised this AD by referencing Airbus Technical Adaptation 
80491184/005/2018, Issue 1, dated February 08, 2018, in lieu of Figure 
A GCAAA--Sheet 02 of Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017, wherever it is appropriate.

[[Page 23464]]

Request To Verify the Required Service Information Prior to AD 
Publication

    UAL requested that we verify the latest revision of Service 
Bulletin A320-53-1259 is referenced in this AD prior to final 
publication. UAL indicated its preference not to request an AMOC 
allowing use of a later revision of the service information immediately 
after AD publication.
    We agree and have confirmed that Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, is the latest version of 
the service information. We have not changed this AD in this regard.

Request To Expand the Airplanes Specified in Paragraph (o) of the 
Proposed AD

    UAL requested that we expand the airplanes specified in paragraph 
(o) of the proposed AD to include all angles that were replaced using 
any service information issued prior to Airbus Service Bulletin A320-
53-1259, Revision 03, dated November 30, 2017, unless maintenance 
records show that the correct rivets were previously installed. UAL 
pointed out that revisions issued prior to Airbus Service Bulletin 
A320-53-1259, Revision 02, dated March 24, 2016, did not specify any 
procedures to install rivets to the keel beam side panel. UAL mentioned 
that it could then be possible that an angle replacement done 
previously using Airbus Service Bulletin A320-53-1259, dated November 
6, 2012, or Airbus Service Bulletin A320-53-1259, Revision 01, dated 
November 26, 2013, might have missing or incorrect rivets installed.
    We disagree with the request to expand the affected airplanes 
specified in paragraph (o) of this AD. As discussed previously, we have 
clarified that the affected airplanes specified in paragraph (o) of 
this AD are those on which a modification (replacement of affected 
titanium angles) was done in accordance with Airbus Service Bulletin 
A320-53-1259, Revision 02, dated March 24, 2016, and not airplanes on 
which an inspection was done. Additionally, we have not received any 
information from either EASA or Airbus regarding expanding the scope of 
the potential unsafe condition. The new requirements in this AD are a 
result of incorrect dimensions of the rivet part number provided in 
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 
2016. No such information was provided by Airbus in the previous 
revisions of the service information. We have not changed this AD in 
this regard.

Request for Clarification of Paragraph (o) of the Proposed AD

    DAL requested that, to reduce confusion, we include clarification 
in paragraph (o) of the proposed AD, that EN6081D5 rivets only need to 
be installed in the fastener holes common to the titanium angle and 
belly fairing wall joint. DAL mentioned that paragraph (o) of the 
proposed AD provides relief for the on-wing inspection if it can be 
determined no titanium angles were installed in accordance with Airbus 
Service Bulletin A320-53-1259, Revision 02, dated March 24, 2016, or if 
only EN6081D5 rivets were used to install the titanium angles on that 
airplane. DAL pointed out that the titanium angles are installed using 
both hi-lok fasteners as well as rivets. DAL also indicated that the 
hi-lok fasteners are common to the keel beam panel and the rivets are 
common to the belly fairing walls.
    We agree to clarify. The service information provides specific 
information for a detailed inspection for the rivets on the titanium 
angles and belly fairing shear wall attachments between frames (FR)40 
and FR42. Additionally, as specified previously, Airbus has issued 
Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated February 
08, 2018, as an exception to Figure A GCAAA--Sheet 02 of Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, which we 
have included in this AD. Therefore, in paragraph (o) of this AD, where 
it specifies ``or if only EN6081D5 rivets were used to install the 
titanium angles on that airplane,'' the installation location for 
rivets is on the titanium angles and belly fairing shear wall 
attachments as identified in the service information. Since the service 
information provides this information, we have not changed this AD 
further regarding this issue.

Request To Use Additional Guidance for Correct Fasteners

    DAL requested that we include additional guidance for accomplishing 
the titanium angle replacement. DAL stated that Airbus issued Operator 
Information Telex (OIT) 16-0032, Rev. 00, dated June 3, 2016, that 
specified the required rivets to use for the replacement. DAL also 
mentioned that Airbus issued Technical Adaptation 80170642/022/2017, 
dated April 7, 2017, to Airbus Service Bulletin A320-53-1259, Revision 
02, dated March 24, 2016, which specified the correct rivets for the 
replacement. DAL added that the FAA could provide credit for airplanes 
on which the correct rivets were installed using the OIT or technical 
adaptation.
    We disagree with the request. Paragraph (p)(2) of this AD refers to 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 30, 
2017, and Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated 
February 08, 2018, which provide adequate service information for 
completing the replacement required if any part number EN6081D4 series 
rivet is found during any inspection required by paragraph (o) of this 
AD. This AD corresponds to EASA AD 2018-0091, dated April 20, 2018, 
which does not permit Airbus OIT 16-0032, Rev. 00, dated June 3, 2016, 
and Airbus Technical Adaptation 80170642/022/2017, dated April 7, 2017, 
as methods of compliance. We agree that those documents are not 
acceptable methods of compliance with this AD because those documents 
only specify the part numbers as well as the location and quantity of 
the parts.
    However, we do agree to clarify the statement in paragraph (o) of 
this AD that describes a method of compliance for the actions required 
by paragraph (o) of this AD. Paragraph (o) of this AD provides relief 
for airplanes on which ``it can be determined that no titanium angles 
have been installed on that airplane in accordance with the 
Accomplishment Instructions of Revision 02 of Airbus Service Bulletin 
A320-53-1259, or if only rivets having part number EN6081D5 have been 
used to install the titanium angles.'' We have revised paragraph (o) of 
this AD to clarify that the ``in accordance with the Accomplishment 
Instructions of Revision 02 of Airbus Service Bulletin A320-53-1259'' 
applies to the whole statement.

Clarification of Retained Effective Date for Paragraph (g) of This AD

    In the introductory text of paragraph (g) of the proposed AD we 
retained a compliance time that referred to the effective date of the 
existing AD. However, we did not include the specific date of AD 2014-
20-04. We have revised the introductory text of paragraph (g) of this 
AD to refer to the effective date of AD 2014-20-04 (November 7, 2014).

Clarification of Retained Effective Date for Paragraph (h)(3) of This 
AD

    In paragraph (h)(3) of the proposed AD we retained a compliance 
time that referred to the effective date of the existing AD. However, 
we did not include the effective date of AD 2014-20-04. We have revised 
paragraph (h)(3)

[[Page 23465]]

of this AD to refer to the effective date of AD 2014-20-04 (November 7, 
2014).

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this final rule with the changes described previously and minor 
editorial changes. We have determined that these minor changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for addressing 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 final 
rule.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017. This service information describes procedures for 
repetitive inspections for cracking of the four titanium angles between 
the belly fairing and the keel beam side panel, an inspection for 
cracking of the open holes if any cracking is found in the titanium 
angles, repair or replacement if necessary, and a detailed inspection 
for and replacement of certain rivets (including a rotating probe test 
for cracks in the open holes).
    Airbus has also issued Technical Adaptation 80491184/005/2018, 
Issue 1, dated February 08, 2018. This service information describes a 
correction to Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017.
    This AD also requires Airbus Service Bulletin A320-53-1014, 
Revision 2, dated September 1, 1994, which the Director of the Federal 
Register approved for incorporation by reference as of November 7, 2014 
(79 FR 59636, October 3, 2014).
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

Costs of Compliance

    We estimate that this AD affects 1,250 airplanes of U.S. registry. 
We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
           Labor cost              Parts cost         Cost per product              Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
295 work[dash]hours x $85 per            $1,045  $26,120...................  $32,650,000.
 hour = $25,075 (Retained
 actions from AD 2014-20-04).
Up to 168 work[dash]hours x $85               0  Up to $14,280.............  Up to $17,850,000.
 per hour = Up to $14,280 (New
 actions of this AD).
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary replacement 
that would be required based on the results of the inspection. We have 
no way of determining the number of aircraft that might need this 
replacement:

                                     Estimated Costs of On-Condition Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                                  Labor cost                                     Parts cost \*\      product
----------------------------------------------------------------------------------------------------------------
168 work-hours x $85 per hour = $14,280.......................................              $0          $14,280
----------------------------------------------------------------------------------------------------------------
* We have received no definitive data that would enable us to provide cost estimates for the on-condition parts
  costs.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. Subtitle VII: Aviation Programs, 
describes in more detail the scope of the Agency's authority.
    We are issuing this rulemaking under the authority described in 
Subtitle VII, Part A, Subpart III, Section 44701: ``General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes and 
associated appliances to the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

[[Page 23466]]

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014), and 
adding the following new AD:

2019-08-07 Airbus SAS: Amendment 39-19628; Docket No. FAA-2018-0795; 
Product Identifier 2018-NM-076-AD.

(a) Effective Date

    This AD is effective June 26, 2019.

(b) Affected ADs

    This AD replaces AD 2014-20-04, Amendment 39-17977 (79 FR 59636, 
October 3, 2014) (``AD 2014-20-04'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes specified in 
paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, 
certificated in any category, all manufacturer serial numbers.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -216, -231, -232, and -233 
airplanes.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of cracks at the lower riveting 
of the four titanium angles that connect the belly fairing to the 
keel beam side panels on both sides of the fuselage. We are issuing 
this AD to address cracking of the titanium angles that connect the 
belly fairing to the keel beam side panels on both sides of the 
fuselage, which could affect the structural integrity of the 
airplane.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Modification, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-20-04, with no changes. For Model A320-211 and -231 series 
airplanes, manufacturer serial numbers 003 through 092 inclusive: 
Prior to the accumulation of 12,000 total landings on the airplane, 
or within 300 days after January 10, 1994 (the effective date of AD 
93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 1993)), 
whichever occurs later, modify the belly fairing structure, in 
accordance with the Accomplishment Instructions of an Airbus service 
bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of this 
AD. As of November 7, 2014 (the effective date of AD 2014-20-04), 
use only the Airbus service bulletin specified in paragraph (g)(3) 
of this AD.
    (1) Airbus Industrie Service Bulletin A320-53-1014, dated June 
25, 1992.
    (2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, 
dated May 26, 1993.
    (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994.

(h) Retained Repetitive Inspection, With Updated Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2014-20-04, with updated service information. At the latest of the 
compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD: Do a detailed inspection for cracking of the four 
titanium angles between the belly fairing and the keel beam side 
panel, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1259, dated November 6, 2012; Airbus 
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; 
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017. After the effective date of this AD, only Airbus 
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, 
may be used. Where Airbus Service Bulletin A320-53-1259, Revision 
03, dated November 30, 2017, specifies to refer to Figure A GCAAA--
Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, 
Issue 1, dated February 08, 2018.
    (1) Before the accumulation of 30,000 total flight cycles or 
60,000 total flight hours, whichever occurs first after first flight 
of the airplane.
    (2) Within 30,000 flight cycles or 60,000 flight hours, 
whichever occurs first after modification of the airplane as 
required by paragraph (g) of this AD, or after installation of new 
titanium angles, provided that, prior to installation, a rototest 
for cracking on the open holes has been accomplished with no crack 
findings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012; Airbus 
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; 
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017. After the effective date of this AD, only Airbus 
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, 
may be used. Where Airbus Service Bulletin A320-53-1259, Revision 
03, dated November 30, 2017, specifies to refer to Figure A GCAAA--
Sheet 02, instead use Airbus Technical Adaptation 80491184/005/2018, 
Issue 1, dated February 08, 2018.
    (3) Within 3,000 flight cycles or 6,000 flight hours, whichever 
occurs first after November 7, 2014 (the effective date of AD 2014-
20-04).

(i) Retained Post-Inspection Actions for No Crack Findings, With 
Updated Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2014-20-04, with updated service information. If, during any 
inspection required by paragraph (h) of this AD, there is no crack 
finding: Accomplish the actions specified in either paragraph (i)(1) 
or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (h) of this AD 
at intervals not to exceed 5,000 flight cycles or 10,000 flight 
hours, whichever occurs first.
    (2) Before further flight after the inspection required by 
paragraph (h) of this AD, remove all inspected titanium angles, 
accomplish a rototest for cracking on the open holes and, provided 
no cracks are found, install new titanium angles, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012; Airbus Service Bulletin A320-53-1259, 
Revision 01, dated November 26, 2013; or Airbus Service Bulletin 
A320-53-1259, Revision 03, dated November 30, 2017. After the 
effective date of this AD, only Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, may be used. Where 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 
30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, instead 
use Airbus Technical Adaptation 80491184/005/2018, Issue 1, dated 
February 08, 2018.

(j) Retained Post-Inspection Actions for Any Crack Findings, With 
Updated Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2014-20-04, with updated service information. If, during any 
inspection required by paragraph (h) of this AD, there is any crack 
finding: Before further flight, remove the affected titanium 
angle(s), accomplish a rototest for cracking on the open holes, and, 
provided no cracks are found, install new titanium angles, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1259, dated November 6, 2012; Airbus Service 
Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 
30, 2017. After the effective date of this AD, only Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be 
used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, 
instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, 
dated February 08, 2018.

(k) Retained Post-Installation Repetitive Inspections, With Updated 
Service Information and Revised Compliance Language

    This paragraph restates the requirements of paragraph (k) of AD 
2014-20-04, with updated service information and revised compliance 
language. For airplanes on which new titanium angles were installed 
as specified in paragraph (i)(2) or (j) of this AD: Within 30,000 
flight cycles or 60,000 flight hours, whichever occurs first after 
the installation, accomplish a detailed inspection for cracking of 
the replaced titanium angles between the belly fairing and the keel 
beam side panel, in accordance with the Accomplishment Instructions 
of Airbus

[[Page 23467]]

Service Bulletin A320-53-1259, dated November 6, 2012; Airbus 
Service Bulletin A320-53-1259, Revision 01, dated November 26, 2013; 
Airbus Service Bulletin A320-53-1259, Revision 02, dated March 24, 
2016; or Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017. After the effective date of this AD, only Airbus 
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017, 
may be used. Repeat the inspection thereafter at intervals not to 
exceed 5,000 flight cycles or 10,000 flight hours, whichever occurs 
first. Where Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 
02, instead use Airbus Technical Adaptation 80491184/005/2018, Issue 
1, dated February 08, 2018.

(l) Retained Post-Inspection Actions for Any Crack Findings During 
Post-Installation Inspections, With Updated Service Information

    This paragraph restates the requirements of paragraph (l) of AD 
2014-20-04, with updated service information. If, during any 
inspection as required by paragraph (k) of this AD, there is any 
crack finding: Before further flight, remove the affected titanium 
angles, accomplish a rototest for cracking on the open holes, and, 
provided no cracks are found, install new titanium angles, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1259, dated November 6, 2012; Airbus Service 
Bulletin A320-53-1259, Revision 01, dated November 26, 2013; or 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 
30, 2017. After the effective date of this AD, only Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be 
used. Where Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017, specifies to refer to Figure A GCAAA--Sheet 02, 
instead use Airbus Technical Adaptation 80491184/005/2018, Issue 1, 
dated February 08, 2018.

(m) Retained Corrective Action for Rototest Crack Finding, With Updated 
Contact Information

    This paragraph restates the requirements of paragraph (m) of AD 
2014-20-04, with updated contact information. If, during any 
rototest as required by paragraph (i), (j), or (l) of this AD, any 
crack is found: Before further flight, repair using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus SAS's EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.

(n) Retained No Termination Action for Repetitive Inspections, With No 
Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2014-20-04, with no changes. Repair or replacement of parts as 
specified in this AD does not terminate the repetitive inspections 
required by this AD.

(o) New Requirement of This AD: Detailed Inspection for Certain Rivets

    For airplanes previously modified (replacement of affected 
titanium angles) using the Accomplishment Instructions of Revision 
02 of Airbus Service Bulletin A320-53-1259: At the earlier of the 
times specified in paragraphs (o)(1) and (o)(2) of this AD, do a 
detailed inspection of the rivet installation in the belly fairing 
shear walls and the titanium angles for part number EN6081D4 series 
rivets in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. 
A review of the airplane maintenance records is acceptable to comply 
with the requirements of this paragraph for that airplane, provided 
it can be determined that no titanium angles have been installed on 
that airplane in accordance with the Accomplishment Instructions of 
Revision 02 of Airbus Service Bulletin A320-53-1259, or if only 
rivets having part number EN6081D5 have been used to install the 
titanium angles on that airplane in accordance with the 
Accomplishment Instructions of Revision 02 of Airbus Service 
Bulletin A320-53-1259. Where Airbus Service Bulletin A320-53-1259, 
Revision 03, dated November 30, 2017, specifies to refer to Figure A 
GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/
005/2018, Issue 1, dated February 08, 2018.
    (1) Within 2,000 flight cycles or 4,000 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) Before exceeding 5,000 flight cycles or 10,000 flight hours, 
whichever occurs first after accomplishment of the last inspection 
specified in paragraph (h) of this AD.

(p) New Requirements of This AD: Replacement of Certain Rivets

    If any part number EN6081D4 series rivet is found during any 
inspection required by paragraph (o) of this AD, before further 
flight, do the actions specified in paragraphs (p)(1) and (p)(2) of 
this AD.
    (1) Remove the part number EN6081D4 series rivets and do a 
rotating probe test of the open holes for cracks, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017. If any crack is found 
during any inspection required by this paragraph, before further 
flight, obtain corrective actions approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus SAS's EASA DOA; and accomplish the corrective actions within 
the compliance time specified therein. If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (2) Replace part number EN6081D4 series rivets with part number 
EN6081D5 series rivets in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017. Where Airbus Service Bulletin A320-53-1259, 
Revision 03, dated November 30, 2017, specifies to refer to Figure A 
GCAAA--Sheet 02, instead use Airbus Technical Adaptation 80491184/
005/2018, Issue 1, dated February 08, 2018.

(q) Service Information Exception

    Where the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1259, Revision 03, dated November 30, 2017, specify to 
install titanium angle part numbers D5337060121200 and 
D5337060121400, this AD allows the installation of titanium angle 
part numbers D5337060121295 and D5337060121495, respectively.

(r) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the International Section, send it to the attention of 
the person identified in paragraph (s)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#8fb6a2cec1c2a2bebeb9a2cec2c0cca2ddcadedacadcdbdccfe9eeeea1e8e0f9"><span class="__cf_email__" data-cfemail="93aabed2dddebea2a2a5bed2dedcd0bec1d6c2c6d6c0c7c0d3f5f2f2bdf4fce5">[email&#160;protected]</span></a>.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 2014-20-04, are approved 
as AMOCs for the corresponding provisions of this AD.
    (2) Contacting the Manufacturer: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): If any service information 
contains procedures or tests that are identified as RC, those 
procedures and tests must be done to comply with this AD; any 
procedures or tests that are not identified as RC are recommended. 
Those procedures and tests that are not identified as RC may be 
deviated from using accepted methods in accordance with the 
operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(s) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2018-0091, dated April 20, 2018, for related 
information. This MCAI may be found in the AD docket on the internet 
at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket 
No. FAA-2018-0795.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and 
fax: 206-231-3223.

(t) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.

[[Page 23468]]

    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (3) The following service information was approved for IBR on 
June 26, 2019.
    (i) Airbus Service Bulletin A320-53-1259, Revision 03, dated 
November 30, 2017.
    (ii) Airbus Technical Adaptation 80491184/005/2018, Issue 1, 
dated February 08, 2018. The date appears only on the last page of 
the document.
    (4) The following service information was approved for IBR on 
November 7, 2014 (79 FR 59636, October 3, 2014).
    (i) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994, including supplementary page 7A. Pages 1 through 
3, 15, 19, 20, and 25 of this document are identified as Revision 2, 
dated September 1, 1994; pages 4 through 8, 10, 12, 16 through 18, 
and 21 through 24 are identified as Revision 1, dated May 26, 1993; 
and pages 9, 11, 13, 14, and 26 are identified as the original, 
dated June 25, 1992.
    (ii) [Reserved]
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; phone: +33 5 61 93 36 96; fax: 
+33 5 61 93 44 51; email: <a href="/cdn-cgi/l/email-protection#f8999b9b978d968cd699918a8f978a8c90d59d998bb899918a9a8d8bd69b9795"><span class="__cf_email__" data-cfemail="cfaeacaca0baa1bbe1aea6bdb8a0bdbba7e2aaaebc8faea6bdadbabce1aca0a2">[email&#160;protected]</span></a>; internet: 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    (6) You may view this service information at the FAA, Transport 
Standards Branch, 2200 South 216th St., Des Moines, WA. For 
information on the availability of this material at the FAA, call 
206-231-3195.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <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 April 10, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-10653 Filed 5-21-19; 8:45 am]
BILLING CODE 4910-13-P