[Federal Register Volume 85, Number 61 (Monday, March 30, 2020)]
[Rules and Regulations]
[Pages 17490-17494]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2020-06504]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0717; Product Identifier 2019-NM-133-AD; Amendment 
39-19879; AD 2020-06-10]
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: The FAA is adopting a new airworthiness directive (AD) for 
certain Airbus SAS Model A318 series 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. This AD was prompted 
by a report of cracking found on the frame of the right-hand side 
sliding window in the flight deck. This AD requires repetitive 
inspections for cracking of the vertical stiffeners of the left- and 
right-hand sides of the window frames and corrective actions if 
necessary, as specified in a European Union Aviation Safety Agency 
(EASA) AD, which is incorporated by reference. The FAA is issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective May 4, 2020.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 4, 2020.

ADDRESSES: For the EASA material incorporated by reference (IBR) in 
this AD, contact the EASA, Konrad-Adenauer-Ufer 3, 50668 Cologne, 
Germany; telephone +49 221 89990 1000; email ADs@easa.europa.eu; 
internet www.easa.europa.eu. You may find this IBR material on the EASA 
website at https://ad.easa.europa.eu.
    For the Airbus material incorporated by reference in this AD, 
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile 
Dewoitine No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 
96; fax +33 5 61 93 44 51; email account.airworth-eas@airbus.com; 
internet https://www.airbus.com.
    You may view this IBR material 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 in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0717.

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-2019-
0717; 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 is U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE, Washington, DC 20590.

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

SUPPLEMENTARY INFORMATION: 

Discussion

    The EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2019-0173, dated July 18, 2019 
(``EASA AD 2019-0173'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus SAS Model A318 series airplanes; Model 
A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes; Model 
A320-211, -212, -214, -215, -216, -231, -232, and -233 airplanes; and 
Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes. 
Model A320-215 airplanes are not on the U.S. Register; this AD 
therefore does not include those airplanes in the applicability.
    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 by adding an AD that would apply to certain Airbus SAS 
Model A318 series airplanes; Model A319-111, -112, -113, -114, -115, -
131, -132, and -133 airplanes; Model A320-211, -212, -214, -215, -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 October 28, 2019 (84 FR 57660). The NPRM was prompted by a 
report of cracking found on the frame of the right-hand side sliding 
window in the flight deck. The NPRM proposed to require repetitive 
inspections for cracking of the vertical stiffeners of the left- and 
right-hand sides of the window frames and corrective actions if 
necessary.
    The FAA is issuing this AD to address cracking of the vertical 
stiffeners of the left- and right-hand sides of the window frames, 
which could affect the structural integrity of the airplane. See the 
MCAI for additional background information.

Comments

    The FAA 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.

Support for the NPRM

    Delta Airlines (DAL) stated its concurrence with the intent of the 
NPRM.

Request To Allow the Use of Additional Service Information

    Airbus asked to allow the use of the following Airbus technical 
adaptations (TAs) during accomplishment of the related Airbus service 
bulletins (as identified only in section 13 of each TA), noting that 
they pertain to an RC (required for compliance) section of the 
applicable service information. Airbus stated that the TAs will ensure 
that the

[[Page 17491]]

eccentric is properly reinstalled in the sliding window frame after 
removal.

 Airbus TA 80662272/007/2019, Issue 1, dated August 29, 2019 
(Airbus Service Bulletin A320-53-1402, dated May 17, 2018)
 Airbus TA 80662272/008/2019, Issue 1, dated August 29, 2019 
(Airbus Service Bulletin A320-53-1403, dated May 17, 2018)
 Airbus TA 80662272/009/2019, Issue 1, dated August 29, 2019 
(Airbus Service Bulletin A320-53-1406, dated May 17, 2018)
 Airbus TA 80662272/010/2019, Issue 1, dated August 29, 2019 
(Airbus Service Bulletin A320-53-1407, dated May 17, 2018)
 Airbus TA 80696258/006/2019, Issue 1, dated October 29, 2019 
(Airbus Service Bulletin A320-53-1404, dated May 17, 2018)
 Airbus TA 80696258/007/2019, Issue 1, dated October 29, 2019 
(Airbus Service Bulletin A320-53-1405, dated May 17, 2018)

    The FAA agrees with the commenter's request for the reason 
provided. The FAA has added paragraph (h)(4) to this AD to reference 
these TAs.
    Airbus also asked that the requirements in the proposed AD related 
to these TAs be defined more robustly than merely referring to EASA AD 
2019-0173.
    The FAA partially agrees. Paragraph (h)(4) of this AD is an 
exception to EASA AD 2019-0173 and references the service information 
specified in EASA AD 2019-0173. Paragraph (h)(4) of this AD has been 
revised to clarify the use of the TAs when complying with the 
requirements of this AD.

Request To Add an Airworthiness Limitations Item (ALI) Task

    United Airlines (UAL) asked to add ALI Task 531136 to the proposed 
AD, to accomplish with the inspection specified in Airbus Service 
Bulletins A320-53-1402 and A320-53-1403, both dated May 17, 2018. UAL 
stated that ALI Task 531136 is a new inspection task introduced in 
Revision 46 of the maintenance planning document (MPD), and that Airbus 
has cancelled ALI Task 531133 in airworthiness limitations section 
(ALS) Part 2, Revision 8. UAL noted that Airbus TFU/ISI 53.11.00.018 
can be referenced for additional information. UAL added that if ALI 
Task 531133 remains active, there will be duplicate inspection 
requirements for the same location (the vertical stiffeners).
    The FAA does not agree with the commenter's request. ALS Part 2, 
Revision 8, might be mandatory for certain airplanes, but not for all 
U.S-registered airplanes. The compliance time for certain airplane 
configurations provided in Appendix 1 of EASA AD 2019-0173 is for 
inspections performed using ALI Task 531133. The FAA has not received 
any information from EASA or Airbus that ALI Task 531133 should be 
replaced with ALI Task 531136. Paragraph (6) of EASA AD 2019-0173, 
specifies that accomplishment of the inspection per ALI Task 531133-02-
1 on an airplane within the threshold and intervals as defined in 
paragraph (1) of EASA AD 2019-0173, constitutes an acceptable method to 
comply with the requirements of paragraph (1) of EASA AD 2019-0173 for 
that airplane. Therefore, no duplication of the inspection requirements 
will occur. The AD has not been changed in this regard.

Request for Confirmation That Inspections Are Required Using Both EASA 
AD 2019-0173 and Applicable Repair Design Approval Sheet (RDAS)

    DAL requested confirmation that when an RDAS exists for a repair of 
the referenced inspection area, the inspection must be accomplished per 
both the requirements in EASA AD 2019-0173, and each applicable RDAS. 
DAL stated that paragraph (5) of EASA AD 2019-0173 states that aircraft 
inspected and repaired before the effective date of the proposed AD per 
the instructions documented in an RDAS should ``accomplish the next due 
inspection for each repaired area in accordance with, and within the 
time period after repair, as specified in Airbus RDAS, as applicable.'' 
DAL stated that it recognizes that this does not terminate the 
inspection criteria. DAL further noted that, if this interpretation is 
correct, a duplicate inspection requirements is created, which could 
ultimately result in inspection in the same area twice at the same 
maintenance check.
    The FAA acknowledges DAL's request and has determined that 
clarification is necessary. The FAA agrees that the requirements of 
paragraph (5) of EASA AD 2019-0173 do not terminate the repetitive 
inspection requirements of paragraph (1) of EASA AD 2019-0173. The FAA 
also agrees that there may be duplicate requirements for inspections in 
accordance with paragraphs (1) and (5) of the EASA AD; however, if the 
description and compliance time for the special detailed inspection 
required by the RDAS and paragraph (1) of the EASA AD are identical, 
operators need not perform duplicate inspections. If there are 
differences between the inspection requirements in the RDAS and EASA AD 
paragraph (1), operators can contact the manufacturer for an 
alternative method of compliance approved by the FAA, EASA, or EASA's 
Design Organization Approval (DOA). The AD has not been changed in this 
regard.

Request To Revise Reporting Requirement

    DAL asked that the reporting requirement in paragraph (h)(3) of the 
proposed AD be revised to require reporting of only positive findings, 
in lieu of both positive and negative findings. DAL stated that, based 
on substantial cyclical data collected through accomplishment of ALI 
Task 531133 and multiple reports of positive cracking indications, 
Airbus has been able to develop and publish standardized repair 
instructions for cracking, which have been incorporated into 
modification service information. DAL added that, since a sufficient 
amount of data has been collected over time to develop these standard 
repairs and modifications, only positive findings should be reported. 
DAL concluded that, as long as accomplishment of ALI Task 531133 
yielded positive findings, paragraph (h)(3)(ii) of the proposed AD 
should include a statement that only positive findings should be 
reported for inspections done before the effective date of the AD.
    DAL also requested that, if revising paragraph (h)(3) of the 
proposed AD to specify reporting of positive inspection findings only, 
the FAA revise paragraph (h)(3)(ii) to include a statement that only 
positive findings for inspections accomplished prior to the effective 
date of the AD require reporting.
    The FAA does not agree with the commenter's requests. The FAA has 
received no information suggesting that sufficient data has been 
collected to exclude reports of negative findings. EASA AD 2019-0173 
requires repetitive inspections after accomplishing the modification, 
and there is no terminating action for those inspections. Further, DAL 
provided no substantiating data to support its assertion that, so long 
as cracking found during ALI Task 531133 inspections was the driver for 
inspections using the specified inspection service information, 100 
percent of crack findings were found during inspections performed using 
inspection service information implemented before the effective date of 
this AD. Therefore, the AD has not been changed in this regard.

[[Page 17492]]

Conclusion

    The FAA 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. The FAA has determined that these minor 
changes:
     Are consistent with the intent that was proposed in the 
NPRM for addressing the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    The FAA also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this final 
rule.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2019-0173 describes procedures for repetitive inspections 
for cracking of the vertical stiffeners of the left- and right-hand 
sides of the window frame, and corrective actions if necessary. 
Corrective actions include modification, rework, and repair.
    Airbus issued the following TAs, which provide missing torque 
values used during reinstallation of the eccentric in the sliding 
window frame. These TAs are distinct since they provide torque values 
used in reinstallation of the eccentric using service information 
specified in EASA AD 2019-0173 (service information that applies to 
different actions and locations).
     Airbus TA 80662272/007/2019, Issue 1, dated August 29, 
2019.
     Airbus TA 80662272/008/2019, Issue 1, dated August 29, 
2019.
     Airbus TA 80662272/009/2019, Issue 1, dated August 29, 
2019.
     Airbus TA 80662272/010/2019, Issue 1, dated August 29, 
2019.
     Airbus TA 80696258/006/2019, Issue 1, dated October 29, 
2019.
     Airbus TA 80696258/007/2019, Issue 1, dated October 29, 
2019.
    This material 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

    The FAA estimates that this AD affects 988 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
                          Labor cost                              Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
11 work-hours x $85 per hour = $935..........................              $0             $935         $923,780
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it takes about 1 work-hour per product to 
comply with the reporting requirement in this AD. The average labor 
rate is $85 per hour. Based on these figures, the FAA estimates the 
cost of reporting the inspection results on U.S. operators to be 
$83,980, or $85 per product.
    The FAA estimates the following costs to do any necessary on-
condition modifications that would be required based on the results of 
any required actions. The FAA has no way of determining the number of 
aircraft that might need this on-condition modification:

                                  Estimated Costs of On-Condition Modification
----------------------------------------------------------------------------------------------------------------
                                                                                                     Cost per
                                  Labor cost                                       Parts cost        product
----------------------------------------------------------------------------------------------------------------
5 work-hours x $85 per hour = $425............................................             (*)           $425 *
----------------------------------------------------------------------------------------------------------------
* The FAA has received no definitive data that would enable the agency to provide parts cost estimates for the
  on-condition modification specified in this AD.

    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the other on-condition actions 
specified in this AD.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to 
Information Collection Clearance Officer, Federal Aviation 
Administration, 10101 Hillwood Parkway, Fort Worth, TX 76177-1524.

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.
    The FAA is 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.

Regulatory Findings

    This AD will not have federalism implications under Executive Order

[[Page 17493]]

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) Will not affect intrastate aviation in Alaska, and
    (3) 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):

2020-06-10 Airbus SAS: Amendment 39-19879; Docket No. FAA-2019-0717; 
Product Identifier 2019-NM-133-AD.

(a) Effective Date

    This AD is effective May 4, 2020.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to Airbus SAS Model airplanes specified in 
paragraphs (c)(1) through (4) of this AD, certificated in any 
category, as identified in European Union Aviation Safety Agency 
(EASA) AD 2019-0173, dated July 18, 2019 (``EASA AD 2019-0173'').
    (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 a report of cracking found on the frame 
of the right-hand side sliding window in the flight deck. The FAA is 
issuing this AD to address cracking of the vertical stiffeners of 
the left- and right-hand sides of the window frames, which could 
affect the structural integrity of the airplane.

(f) Compliance

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

(g) Requirements

    Except as specified in paragraph (h) of this AD: Comply with all 
required actions and compliance times specified in, and in 
accordance with, EASA AD 2019-0173.

(h) Exceptions to EASA AD 2019-0173

    (1) Where EASA AD 2019-0173 refers to its effective date, this 
AD requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2019-0173 does not apply 
to this AD.
    (3) Paragraph (4) of EASA AD 2019-0173 specifies to report 
inspection results to Airbus within a certain compliance time. For 
this AD, report inspection results at the applicable time specified 
in paragraph (h)(3)(i) or (ii) of this AD.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 90 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 90 days after the effective date 
of this AD.
    (4) This AD allows the use of the torque values specified in 
Section 13 of the Airbus technical adaptations (TAs) identified in 
paragraphs (h)(4)(i) through (vi) of this AD, when installing a 
certain eccentric referenced in the applicable Airbus service 
bulletin, as specified in the applicable TA.
    (i) Airbus TA 80662272/007/2019, Issue 1, dated August 29, 2019.
    (ii) Airbus TA 80662272/008/2019, Issue 1, dated August 29, 
2019.
    (iii) Airbus TA 80662272/009/2019, Issue 1, dated August 29, 
2019.
    (iv) Airbus TA 80662272/010/2019, Issue 1, dated August 29, 
2019.
    (v) Airbus TA 80696258/006/2019, Issue 1, dated October 29, 
2019.
    (vi) Airbus TA 80696258/007/2019, Issue 1, dated October 29, 
2019.

(i) 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 (j) of this AD. Information may 
be emailed to: 9-ANM-116-AMOC-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 instructions from a manufacturer, the instructions must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus SAS's 
EASA Design Organization Approval (DOA). If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): For any service information 
referenced in EASA AD 2019-0173 that contains RC procedures and 
tests: Except as required by paragraph (i)(2) of this AD, RC 
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.
    (4) Paperwork Reduction Act Burden Statement: A federal agency 
may not conduct or sponsor, and a person is not required to respond 
to, nor shall a person be subject to a penalty for failure to comply 
with a collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 1 
hour per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory as 
required by this AD; the nature and extent of confidentiality to be 
provided, if any. Send comments regarding this burden estimate or 
any other aspect of this collection of information, including 
suggestions for reducing this burden to Information Collection 
Clearance Officer, Federal Aviation Administration, 10101 Hillwood 
Parkway, Fort Worth, TX 76177-1524.

(j) Related Information

    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.

(k) 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.

[[Page 17494]]

    (i) European Union Aviation Safety Agency (EASA) AD 2019-0173, 
dated July 18, 2019.
    (ii) Airbus Technical Adaptation 80662272/007/2019, Issue 1, 
dated August 29, 2019.
    (iii) Airbus Technical Adaptation 80662272/008/2019, Issue 1, 
dated August 29, 2019.
    (iv) Airbus Technical Adaptation 80662272/009/2019, Issue 1, 
dated August 29, 2019.
    (v) Airbus Technical Adaptation 80662272/010/2019, Issue 1, 
dated August 29, 2019.
    (vi) Airbus Technical Adaptation 80696258/006/2019, Issue 1, 
dated October 29, 2019.
    (vii) Airbus Technical Adaptation 80696258/007/2019, Issue 1, 
dated October 29, 2019.
    (3) For information about EASA AD 2019-0173, contact the EASA, 
Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; telephone +49 221 
89990 6017; email ADs@easa.europa.eu; internet www.easa.europa.eu. 
You may find this EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) For information about the Airbus service information 
incorporated by reference in this AD, contact Airbus SAS, 
Airworthiness Office--EIAS, Rond-Point Emile Dewoitine No: 2, 31700 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 
44 51; email account.airworth-eas@airbus.com; internet https://www.airbus.com.
    (5) You may view this material 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. This 
material may be found in the AD docket on the internet at https://www.regulations.gov by searching for and locating Docket No. FAA-
2019-0717.
    (6) You may view this material that is incorporated by reference 
at the National Archives and Records Administration (NARA). For 
information on the availability of this material at NARA, email 
fedreg.legal@nara.gov, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued on March 16, 2020.
Gaetano A. Sciortino,
Deputy Director for Strategic Initiatives, Compliance & Airworthiness 
Division, Aircraft Certification Service.
[FR Doc. 2020-06504 Filed 3-27-20; 8:45 am]
 BILLING CODE 4910-13-P


