[Federal Register Volume 84, Number 128 (Wednesday, July 3, 2019)]
[Rules and Regulations]
[Pages 31710-31713]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-14152]



[[Page 31710]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0020; Product Identifier 2018-NM-144-AD; Amendment 
39-19659; AD 2019-12-04]
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 superseding Airworthiness Directive (AD) 2018-19-
18, which applied to certain Airbus SAS Model A300 B4-603, B4-620, and 
B4-622 airplanes; Model A300 B4-600R series airplanes; Model A300 C4-
605R Variant F airplanes; and Model A300 F4-605R airplanes. AD 2018-19-
18 required, depending on airplane configuration, a modification of 
certain angle fitting attachment holes; repetitive inspections for 
cracking of certain holes of the internal lower angle fitting web, 
certain holes of the internal lower angle fitting horizontal splicing, 
the aft bottom panel, and a certain junction area; and related 
investigative and corrective actions if necessary. This new AD retains 
those actions, expands the applicability, and, for certain airplanes, 
requires repetitive inspections for cracking of certain holes of the 
center wing box (CWB) lower angle fittings and the CWB lower panel, and 
corrective actions if necessary, as specified in an European Aviation 
Safety Agency (EASA) AD, which is incorporated by reference. This AD 
was prompted by reports of cracking of a certain frame (FR) angle 
fitting. The FAA is issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective August 7, 2019.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of August 7, 
2019.

ADDRESSES: For the material incorporated by reference (IBR) in this AD, 
contact the EASA, at Konrad-Adenauer-Ufer 3, 50668 Cologne, Germany; 
telephone +49 221 89990 1000; email [email protected]; internet 
www.easa.europa.eu. You may find this IBR material on the EASA website 
at https://ad.easa.europa.eu. 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 
http://www.regulations.gov.

Examining the AD Docket

    You may examine the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0020; 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: Dan Rodina, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 2200 South 
216th St., Des Moines, WA 98198; telephone and fax 206-231-3225.

SUPPLEMENTARY INFORMATION: 

Discussion

    The FAA issued a notice of proposed rulemaking (NPRM) to amend 14 
CFR part 39 to supersede AD 2018-19-18, Amendment 39-19418 (83 FR 
49793, October 3, 2018) (``AD 2018-19-18''). AD 2018-19-18 applied to 
certain Airbus SAS Model A300 B4-603, B4-620, and B4-622 airplanes; 
Model A300 B4-600R series airplanes; Model A300 C4-605R Variant F 
airplanes; and Model A300 F4-605R airplanes. The NPRM published in the 
Federal Register on February 15, 2019 (84 FR 4387). The NPRM was 
prompted by the determination that additional airplanes may be affected 
by the unsafe condition. The NPRM proposed to continue to require, 
depending on airplane configuration, a modification of certain angle 
fitting attachment holes; repetitive inspections for cracking of 
certain holes of the internal lower angle fitting web, certain holes of 
the internal lower angle fitting horizontal splicing, the aft bottom 
panel, and a certain junction area; and related investigative and 
corrective actions if necessary. The NPRM also proposed to expand the 
applicability, and, for certain airplanes, proposed to require 
repetitive inspections for cracking of certain holes of the CWB lower 
angle fittings and the CWB lower panel, and corrective actions if 
necessary. The FAA is issuing this AD to address cracking of the FR47 
angle fitting, which could result in reduced structural integrity of 
the airplane.
    EASA, which is the Technical Agent for the Member States of the 
European Union, has issued EASA AD 2018-0229, dated October 23, 2018 
(``EASA AD 2018-0229'') (also referred to as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus SAS Model A300 B4-603, B4-620, B4-622, B4-
605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes. The 
MCAI states:

    Prompted by cracks found on CWB FR47 angle fittings, Airbus 
issued SB [service bulletin] A300-57-6049, SB A300-57-6050, and SB 
A300-57-6086.
    These cracks, if not detected and corrected, could affect the 
structural integrity of the CWB of the aeroplane.
    Consequently, DGAC [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] France published AD 94-241-170, AD 1999-147-279, 
AD 2000-533-328 and AD F-2004-159 (EASA approval 2004-9779), each 
[DGAC France] AD superseding the previous one, to require repetitive 
high frequency eddy current (HFEC) rotating probe inspections of the 
FR47 internal lower angle fitting.
    After DGAC France AD F-2004-159 was issued, cracks were 
reportedly found on the horizontal flange of the FR47 internal 
corner angle fitting during accomplishment of routine maintenance 
structural inspection and modification in accordance with the 
instructions of Airbus SB A300-57-6050. Prompted by these findings, 
Airbus reviewed and amended the inspection programme for the 
internal lower angle fitting flange (horizontal face).
    Consequently, EASA issued AD 2012-0092 [which corresponds to FAA 
AD 2014-20-18, Amendment 39-17991 (79 FR 65879, November 6, 2014) 
(``AD 2014-20-18'')] retaining the requirements of DGAC France AD F-
2004-159, which was superseded, and requiring additional repetitive 
inspections of the CWB lower panel through the ultrasonic method 
and, depending on findings, re-installation of removed fasteners in 
transition fit instead of interference. In addition, DGAC France had 
previously issued AD F-2005-124 (EASA approval 2005-6071) to require 
CWB FR47 angle fittings inspections for A300 F4-608ST aeroplanes, in 
accordance with Airbus SB A300-57-9001 and SB A300-57-9002.
    Following the discovery of numerous cracks during the 
accomplishment of SB A300-57-6049 and SB A300-57-6086 inspections, 
Airbus developed in a first step a new (recommended) modification 
(Airbus SB A300-57-6113), defined associated inspections programme 
and methods (ultrasonic/radiographic), and published SB A300-57-
6119. Consequently, EASA issued AD 2016-0198, retaining the 
requirements of EASA AD 2012-0092, which was superseded, to require 
repetitive inspections for post-SB A300-57-6113 aeroplanes.
    After EASA AD 2016-0198 was issued, Airbus revised in a second 
step the inspection programme for A300-600 pre-SB

[[Page 31711]]

A300-57-6113 and A300-600ST aeroplanes, reducing inspection 
thresholds and intervals. At this opportunity, the existing 
ultrasonic inspection of the CWB lower panel for A300-600 aeroplanes 
was added for A300-600ST aeroplanes. Consequently, EASA issued AD 
2017-0210 [which corresponds to FAA AD 2018-19-18] retaining the 
requirements of EASA AD 2016-0198 for A300-600 aeroplanes and DGAC 
France AD F-2005-124 for A300-600ST aeroplanes, which were both 
superseded, to include these new requirements.
    Since EASA AD 2017-0210 was issued, Airbus revised in a third 
step the inspection programme for A300-600 post-mod 12171 and post-
mod 12249 reducing inspection thresholds and intervals, and 
introducing the CWB lower panel inspection. Airbus published SB 
A300-57-6121, superseding Airworthiness Limitation Items (ALI) tasks 
571012 & 571014.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2017-0210, which is superseded, and expands 
the Applicability (Group 3) to include post-mod 12171 and post-mod 
12249 aeroplanes [and requires sending inspection results to 
Airbus].

    You may examine the MCAI in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2019-
0020.

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.

Request To Extend Grace Period for Certain Inspections

    United Parcel Service (UPS) requested that the grace periods 
specified in Note 6 and Note 8 of EASA AD 2018-0229 for the inspections 
specified in paragraph (7) and paragraph (9) of EASA AD 2018-0229 be 
extended to 30 months after the effective date of the AD, or 18,700 
flight cycles, whichever occurs later. UPS reasoned that the proposed 
AD is being issued to supersede AD 2018-19-18 in order to add airplanes 
that are post-modification 12171 and 12249. UPS noted that post-
modification 12171 and 12249 airplanes have not had any crack findings 
in service, and that previous related ADs were issued as a result of 
inferior fatigue characteristics compared to airplanes that are post-
modification 12171. UPS pointed out that, of the inspections it has 
completed so far, there have not been any findings that require part 
replacement or major repairs. UPS also reasoned that the airworthiness 
limitation item inspections that the service information is superseding 
are not required until 18,700 flight cycles at the earliest. Further, 
UPS asserted that the proposed grace period would require UPS to send 
airplanes to a maintenance facility on a special visit to accomplish 
this inspection. UPS maintained that the suggested grace period would 
provide an equivalent level of safety for the proposed action.
    The FAA does not agree with the commenter's request to extend the 
proposed grace period. In developing an appropriate compliance time for 
this action, the FAA considered the urgency associated with the subject 
unsafe condition based on similarly affected models and information 
received from EASA. In addition, the FAA considered the practical 
aspect of accomplishing the required modification within a period of 
time that corresponds to the normal scheduled maintenance for most 
affected operators. In consideration of these factors, the FAA has 
determined that a 12-month grace period will ensure an acceptable level 
of safety. However, under the provisions of paragraph (k)(1) of this 
AD, the FAA will consider requests for approval of an extension of the 
grace period if sufficient data are submitted to substantiate that the 
new grace period would provide an acceptable level of safety. The FAA 
has not changed this AD in this regard.

Request To Use Later Approved Revisions of Certain Service Information

    FedEx requested clarification to determine if a statement in EASA 
AD 2018-0229 is applicable to this AD, and if all later approved 
service information revisions are acceptable for compliance with this 
AD. FedEx pointed out that the Reference Publications section of EASA 
AD 2018-0229 allows the use of later approved revisions to the 
specified service information for compliance.
    The FAA agrees to clarify. This AD does not exclude the Reference 
Publications section of the MCAI. Therefore, this AD does not disallow 
the ``later approved revisions'' language typically used in EASA ADs. 
The FAA has not changed this AD in this regard.

Request To Reference Latest Service Information

    FedEx requested that Airbus Service Bulletin A300-57-6086, Revision 
7, dated March 26, 2018, be allowed as acceptable for compliance with 
the requirements of the proposed AD. FedEx pointed out that EASA AD 
2018-0229 references Airbus Service Bulletin A300-57-6086, Revision 6, 
dated July 4, 2017, which has since been revised to Airbus Service 
Bulletin A300-57-6086, Revision 7, dated March 26, 2018, noting that AD 
2018-19-18 allows the use of Airbus Service Bulletin A300-57-6086, 
Revision 7, dated March 26, 2018.
    In response, the FAA notes that this AD refers to the MCAI for 
compliance, which in turn refers to the service information that is the 
required for accomplishing the required actions. As stated previously, 
this AD does not exclude the Reference Publications section of the 
MCAI. Therefore, this AD does not disallow the ``later approved 
revisions'' language typically used in EASA ADs. Therefore, no change 
to this AD is necessary in this regard.

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 as proposed, except for 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.

Related IBR Material Under 1 CFR Part 51

    EASA AD 2018-0229, dated October 23, 2018, describes procedures for 
a modification of the angle fitting attachment holes, an inspection of 
certain holes of the internal lower angle fitting web for cracking, an 
inspection of certain holes of the internal lower angle fitting 
horizontal splicing for cracking, an inspection of the aft bottom panel 
for cracking, an inspection of the FR47/Rib 1 junction area for 
cracking, an inspection of certain holes of the CWB lower angle 
fittings for cracking, an inspection of the CWB lower panel for 
cracking, and corrective actions. The corrective actions include a 
rotating probe inspection for cracking, replacing damaged fasteners, 
reaming and drilling holes, installing the next nominal fastener for 
oversized bore holes, and repairing cracks. 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 65 airplanes of U.S. 
registry. The FAA estimates the following costs to comply with this AD:

[[Page 31712]]



                                     Estimated Costs for Required Actions *
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            Action                Labor cost        Parts cost     Cost per product     Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
Retained actions from AD 2018- Up to 727 work-   Up to $3,370....  Up to $65,165...  Up to $4,235,725.
 19-18.                         hours x $85 per
                                hour = Up to
                                $61,795.
New actions..................  242 work-hours x  $100............  $20,670.........  $1,343,550.
                                $85 per hour =
                                $20,570.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    The FAA estimates that it would take 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 
$5,525, or $85 per product.
    The FAA has received no definitive data that would enable the 
agency to provide cost estimates for the 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 the FAA 
at 800 Independence Ave. SW, Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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.
    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

    The FAA 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) 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 removing Airworthiness Directive (AD) 
2018-19-18, Amendment 39-19418 (83 FR 49793, October 3, 2018), and 
adding the following new AD:

2019-12-04 Airbus SAS: Amendment 39-19659; Docket No. FAA-2019-0020; 
Product Identifier 2018-NM-144-AD.

(a) Effective Date

    This AD is effective August 7, 2019.

(b) Affected ADs

    (1) This AD replaces AD 2018-19-18, Amendment 39-19418 (83 FR 
49793, October 3, 2018) (``AD 2018-19-18'').
    (2) This AD affects AD 2014-20-18, Amendment 39-17991 (79 FR 
65879, November 6, 2014) (``AD 2014-20-18'').

(c) Applicability

    This AD applies to Airbus SAS Model A300 B4-603, B4-620, B4-622, 
B4-605R, B4-622R, C4-605R Variant F, F4-605R, and F4-622R airplanes, 
certificated in any category, as identified in European Aviation 
Safety Agency (EASA) AD 2018-0229, dated October 23, 2018 (``EASA AD 
2018-0229'').

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of cracking of the frame (FR) 47 
angle fitting. The FAA is issuing this AD to address cracking of the 
FR47 angle fitting, which could result in reduced 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 2018-0229.

(h) Exceptions to EASA AD 2018-0229

    (1) For purposes of determining compliance with the requirements 
of this AD:

[[Page 31713]]

Where EASA AD 2018-0229 refers to its effective date, this AD 
requires using the effective date of this AD.
    (2) The ``Remarks'' section of EASA AD 2018-0229 does not apply 
to this AD.
    (3) Where Note 1 of EASA AD 2018-0229 specifies the grace period 
to be counted from January 6, 2001, this AD requires the grace 
period to be counted from December 19, 2005 (the effective date of 
AD 2005-23-08, Amendment 39-14366 (70 FR 69056, November 14, 2005) 
(``AD 2005-23-08'')).
    (4) Where Note 2 and Note 4 of EASA AD 2018-0229 specify the 
grace periods to be counted from November 7, 2017, without exceeding 
certain inspection thresholds and intervals, the grace periods in 
those Notes for this AD are within 12 months after November 7, 2018 
(the effective date of AD 2018-19-18).
    (5) Paragraph (11) of EASA AD 2018-0229 specifies to report all 
inspection results to Airbus. For this AD, report all inspection 
results to Airbus Service Bulletin Reporting Online Application on 
Airbus World (https://w3.airbus.com/) at the applicable time 
specified in paragraph (h)(5)(i) or (h)(5)(ii) of this AD. The 
report must include the inspection results, the method of 
inspection, the airplane serial number, and the number of flight 
cycles and flight hours on the airplane.
    (i) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (ii) If the inspection was done before the effective date of 
this AD: Submit the report within 30 days after the effective date 
of this AD.

(i) Terminating Action for AD 2014-20-18

    Accomplishment of the action required by paragraph (1) of EASA 
AD 2018-0229 and the initial inspections required by paragraphs (3), 
(4), and (5) of EASA AD 2018-0229 terminates all requirements of AD 
2014-20-18.

(j) Credit for Previous Actions

    This paragraph provides credit for actions required by paragraph 
(1) of EASA AD 2018-0229, if those actions were performed before 
December 19, 2005 (the effective date of AD 2005-23-08) using Airbus 
Service Bulletin A300-57-6050, Revision 02, dated February 10, 2000.

(k) 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 (l)(1) of this AD. Information 
may be emailed to: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain 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 2018-0229 that contains RC procedures and 
tests: Except as required by paragraph (k)(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. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW, Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(l) Related Information

    (1) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone 
and fax 206-231-3225.
    (2) For Airbus service information identified in this AD that is 
not incorporated by reference, contact Airbus SAS, Airworthiness 
Office--EAW, Rond-Point Emile Dewoitine No: 2, 31700 Blagnac Cedex, 
France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 51; email 
[email protected]; internet http://www.airbus.com.

(m) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) European Aviation Safety Agency (EASA) AD 2018-0229, dated 
October 23, 2018.
    (ii) [Reserved]
    (3) For EASA AD 2018-0229, contact the EASA, Konrad-Adenauer-
Ufer 3, 50668 Cologne, Germany; telephone +49 221 89990 6017; email 
[email protected]; Internet www.easa.europa.eu. You may find this 
EASA AD on the EASA website at https://ad.easa.europa.eu.
    (4) You may view this EASA AD 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. EASA AD 
2018-0229 may be found in the AD docket on the internet at http://www.regulations.gov by searching for and locating Docket No. FAA-
2019-0020.
    (5) 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, call 202-
741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Des Moines, Washington, on June 12, 2019.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-14152 Filed 7-2-19; 8:45 am]
BILLING CODE 4910-13-P