
[Federal Register Volume 84, Number 32 (Friday, February 15, 2019)]
[Proposed Rules]
[Pages 4387-4390]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-02552]


=======================================================================
-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2019-0020; Product Identifier 2018-NM-144-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus SAS Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2018-19-
18, which applies 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 requires, 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. Since we issued AD 
2018-19-18, we have determined that additional airplanes are affected 
by the unsafe condition. This proposed AD would retain the actions 
required by AD 2018-19-18, expand the applicability, and, for certain 
airplanes, would require 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. We are proposing this 
AD to address the unsafe condition on these products.

DATES: We must receive comments on this proposed AD by April 1, 2019.

ADDRESSES: You may send comments, using the procedures found in 14 CFR 
11.43 and 11.45, by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: 202-493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE, Washington, DC 20590, between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays.
    For the incorporation by reference (IBR) material described in the 
``Related IBR material under 1 CFR part 51'' section in SUPPLEMENTARY 
INFORMATION, contact European Aviation Safety Agency (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. 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 NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (telephone 800-
647-5527) is in the ADDRESSES section. Comments will be available in 
the AD docket shortly after receipt.

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:

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposal. Send your comments to an address listed 
under the ADDRESSES section. Include ``Docket No. FAA-2019-0020; 
Product Identifier 2018-NM-144-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this NPRM. We will consider all 
comments received by the closing date and may amend this NPRM based on 
those comments.
    We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We 
will also post a report summarizing each substantive verbal contact we 
receive about this NPRM.

Discussion

    We issued AD 2018-19-18, Amendment 39-19418 (83 FR 49793, October 
3, 2018) (``AD 2018-19-18''), for 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 requires, 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. AD 2018-
19-18 resulted from reports of cracking on a certain frame (FR) angle 
fitting. We issued AD 2018-19-18 to address cracking of the FR47 angle 
fitting, which could result in reduced structural integrity of the 
airplane.

Actions Since AD 2018-19-18 Was Issued

    We have determined that additional airplanes are affected by the 
unsafe condition. Airbus SAS Model A300 B4-622R and Model A300 F4-600R 
series airplanes that have accomplished Airbus Modification 12171 and 
Airbus Modification 12249 need to be inspected in order to address the 
unsafe condition.
    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

[[Page 4388]]

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 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.

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 and it is publicly available through the EASA 
website.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI referenced 
above. We are proposing this AD because we evaluated all pertinent 
information and determined an unsafe condition exists and is likely to 
exist or develop on other products of the same type design.

Explanation of Required Compliance Information

    In the FAA's ongoing efforts to improve the efficiency of the AD 
process, the FAA worked with Airbus and EASA to develop a process to 
use certain EASA ADs as the primary source of information for 
compliance with requirements for corresponding FAA ADs. As a result, 
EASA AD 2018-0229 will be incorporated by reference in the FAA final 
rule. This proposed AD would, therefore, require compliance with the 
provisions specified in EASA AD 2018-0229, except for any differences 
identified as exceptions in the regulatory text of this proposed AD. 
Service information specified in EASA AD 2018-0229 that is required for 
compliance with EASA AD 2018-0229 will be available on the internet 
http://www.regulations.gov by searching for and locating Docket No. 
FAA-2019-0020 after the FAA final rule is published.

Explanation of Retained Requirements

    Although this proposed AD does not explicitly restate the 
requirements of AD 2018-19-18, this proposed AD would retain all of the 
requirements of AD 2018-19-18. Those requirements are referenced in 
EASA AD 2018-0229, which, in turn, is referenced in paragraph (g) of 
this proposed AD.

Differences Between This Proposed AD and the MCAI

    EASA AD 2018-0229 does not specify credit for actions previously 
performed with certain service information. However, this proposed AD 
allows for 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 FAA AD 2005-23-08, Amendment 39-14366 (70 FR 
69056, November 14, 2005)) using Airbus Service Bulletin A300-57-6050, 
Revision 02, dated February 10, 2000. We consider those methods to be 
adequate to address the modification of the angle fitting attachment 
holes on the left hand and right hand sides by cold expansion required 
by this proposed AD.

Relationship Between Proposed AD and AD 2014-20-18, Amendment 39-17991 
(79 FR 65879, November 6, 2014) (``AD 2014-20-18'')

    Paragraph (o) of AD 2018-19-18 specifies that accomplishing certain 
actions terminates all requirements of AD 2014-20-18. Because this 
proposed AD will supersede AD 2018-19-18, this terminating action is 
retained in this proposed AD and instead refers to the accomplishment 
of the corresponding actions in EASA AD 2018-0229. Therefore, paragraph 
(i) of this proposed AD specifies that accomplishment of the 
modification required by paragraph (1) of EASA AD 2018-0229 and 
accomplishment of the initial inspections required by paragraphs (3), 
(4), and (5) of EASA AD 2018-0229 terminate all requirements of AD 
2014-20-18.

Costs of Compliance

    We estimate that this proposed AD affects 65 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

[[Page 4389]]



                                     Estimated Costs for Required Actions *
----------------------------------------------------------------------------------------------------------------
            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 = $61,795.
New proposed actions.........  242 work-hours x  $100............  $20,670.........  $1,343,550.
                                $85 per hour =
                                $20,570.
----------------------------------------------------------------------------------------------------------------
* Table does not include estimated costs for reporting.

    We estimate that it would take about 1 work-hour per product to 
comply with the proposed reporting requirement in this proposed AD. The 
average labor rate is $85 per hour. Based on these figures, we estimate 
the cost of reporting the inspection results on U.S. operators to be 
$5,525, or $85 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
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 NPRM is 2120-
0056. The paperwork cost associated with this NPRM 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 NPRM 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.
    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 proposed 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 proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would 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 this proposed 
regulation:
    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.

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 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:

Airbus SAS: Docket No. FAA-2019-0020; Product Identifier 2018-NM-
144-AD.

(a) Comments Due Date

    We must receive comments by April 1, 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 on the frame (FR) 47 
angle fitting. We are 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 4390]]

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 period to be counted from November 7, 2017, without exceeding 
certain inspection thresholds and intervals, the grace period for 
this AD is 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)(2) of this AD. Information 
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
    (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 2018-19-18 are approved as 
AMOCs for the corresponding provisions of EASA AD 2018-0229 that are 
required by paragraph (g) of this AD.
    (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 information about EASA AD 2018-0229, contact 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. 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.
    (2) 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.

    Issued in Des Moines, Washington, on February 1, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2019-02552 Filed 2-14-19; 8:45 am]
BILLING CODE 4910-13-P


