[Federal Register Volume 83, Number 107 (Monday, June 4, 2018)]
[Proposed Rules]
[Pages 25590-25595]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-11822]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to adopt a new airworthiness directive (AD) for 
certain Airbus Model A300 B4-603, B4-620, and B4-622 airplanes; Model 
A300 F4-605R airplanes; Model A300 C4-605R Variant F airplanes; and 
Model A300 B4-600R series airplanes. This proposed AD was prompted by 
reports of cracking on the frame (FR) 47 angle fitting. This proposed 
AD would 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 the FR47/Rib 1 junction area, and related 
investigative 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 July 19, 2018.

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: Deliver to Mail address above between 9 
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus 
SAS, Airworthiness Office--EAW, 1 Rond Point Maurice Bellonte, 31707 
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. You may view this service information at the FAA, 
Transport Standards Branch, 2200

[[Page 25591]]

South 216th St., Des Moines, WA. For information on the availability of 
this material at the FAA, call 206-231-3195.

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-2018-
0497; or in person at the Docket Management Facility between 9 a.m. and 
5 p.m., Monday through Friday, except Federal holidays. The AD docket 
contains this NPRM, the regulatory evaluation, any comments received, 
and other information. The street address for the Docket Operations 
office (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-2018-0497; 
Product Identifier 2017-NM-140-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

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0210, dated October 24, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 B4-603, B4-
620, and B4-622 airplanes; Model A300 F4-605R airplanes; Model A300 C4-
605R Variant F airplanes; and Model A300 B4-600R series airplanes. The 
MCAI states:

    Prompted by cracks found on the Frame (FR) 47 angle fitting, 
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 centre wing box (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 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 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 interface.
    In addition, DGAC France had previously issued AD F-2005-124 
(EASA approval 2005-6071) to require the same 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 A300-57-6089 inspections, 
Airbus developed in a first step a new (recommended) modification 
(Airbus SB A300-57-6113) and defined, for post-mod aeroplanes, new 
inspections, and published SB A300-57-6119, which included new 
inspection methods (ultrasonic/radiographic) with new inspection 
thresholds and intervals.
    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.
    Since EASA AD 2016-0198 was issued, Airbus revised in a second 
step the inspection programme for A300-600 pre-SB 57-6113 and A300-
600ST aeroplanes, reducing inspection thresholds and intervals. At 
this opportunity, the existing ultrasonic inspection for A300-600 
aeroplanes has been added for A300-600ST aeroplanes.
    For the reasons described above, this new [EASA] AD retains the 
requirements of EASA AD 2016-0198 for A300-600 aeroplanes and of 
DGAC France AD F-2005-124 for A300-600ST aeroplanes, which are both 
superseded, and requires [modification through cold expansion of 
certain angle fitting attachment holes and] 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 the FR47/Rib 1 junction area, 
and applicable related investigative and corrective actions] with 
new compliance times and intervals. This [EASA] AD is applicable to 
both A300-600 and A300-600ST aeroplanes * * *.

    Related investigative actions include a rotating probe inspection 
for cracking. Corrective actions include replacing damaged fasteners, 
reaming and drilling holes, installing the next nominal fastener for 
oversized bore holes, and repairing cracks. 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-2018-0497.

Relationship Between Proposed AD and AD 2014-20-18

    This NPRM would not supersede AD 2014-20-18. Rather, we have 
determined that a stand-alone AD would be more appropriate to address 
the changes in the MCAI. This NPRM would require depending on airplane 
configuration, a modification of certain angle fitting attachment 
holes, 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 the FR47/Rib 1 junction 
area. Accomplishment of the proposed modification and initial 
inspections would then terminate all of the requirements of AD 2014-20-
18.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information.
     Service Bulletin A300-57-6049, Revision 8, dated July 4, 
2017. This service information describes procedures for HFEC rotating 
probe inspections for cracking of certain holes of the internal lower 
angle fitting web.
     Service Bulletin A300-57-6086, Revision 6, dated July 4, 
2017. This service information describes procedures for HFEC rotating 
probe inspections for cracking of certain holes in the internal lower 
angle fitting horizontal splicing (left-hand and right-hand sides) and 
for ultrasonic inspections for cracking of the aft bottom panel.
     Service Bulletin A300-57-6119, Revision 00, dated April 
25, 2016. This service information describes procedures for ultrasonic 
and radiographic inspections for cracking of the FR47/Rib 1 junction 
area.
    This service information is reasonably available because the 
interested parties have access to it through their normal

[[Page 25592]]

course of business or by the means identified in the ADDRESSES section.

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 and service 
information 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.

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:

                                      Estimated Costs for Required Actions
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
            Labor cost                      Parts cost                Cost per product            operators
----------------------------------------------------------------------------------------------------------------
Up to 727 work-hours x $85 per     Up to $3,370...............  Up to $65,165..............  Up to $4,235,725
 hour = Up to $61,795.                                                                        per inspection
                                                                                              cycle.
----------------------------------------------------------------------------------------------------------------

    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 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 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 adding the following new airworthiness 
directive (AD):

Airbus: Docket No. FAA-2018-0497; Product Identifier 2017-NM-140-AD.

(a) Comments Due Date

    We must receive comments by July 19, 2018.

(b) Affected ADs

    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 Model A300 B4-603, A300 B4-620, A300 
B4-622, A300 B4-605R, A300 B4-622R, A300 C4-605R Variant F, and A300 
F4-605R airplanes, certificated in any category, all manufacturer 
serial numbers, except airplanes on which Airbus Modification 12171 
or 12249 has been embodied in production, or on which Airbus Service 
Bulletin A300-57-6069 has been embodied in service.

(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 detect and correct cracking 
of FR47 angle fitting, which could

[[Page 25593]]

result in reduced structural integrity of the airplane.

(f) Compliance

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

(g) Definitions

    For the purposes of this AD, the definitions in paragraphs 
(g)(1) through (g)(6) apply.
    (1) Group 1 airplanes are those airplanes on which Airbus 
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, 
has not been incorporated as of the effective date of this AD.
    (2) Group 2 airplanes are those airplanes on which Airbus 
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, 
has been incorporated as of the effective date of this AD.
    (3) The average flight time (AFT) for the inspection threshold 
is defined as the flight hours (FH) divided by the flight cycles 
(FC), counted from the first flight of the airplane.
    (4) The AFT for the inspection interval is defined as the FH 
divided by the FC, counted from the date of the last inspection 
required by paragraph (i), (j), (k), or (l) of this AD, as 
applicable.
    (5) For airplanes on which Airbus modification 10155 has been 
embodied, the thresholds for the inspections required by paragraphs 
(i), (j), and (k) of this AD are counted from the first flight of 
the airplane.
    (6) For airplanes on which Airbus modification 10155 has not 
been embodied, the thresholds for the inspections required by 
paragraphs (i), (j), and (k) of this AD are counted since the date 
on which Airbus Service Bulletin A300-57-6050 was embodied on the 
airplane.

(h) Modification

    For all airplanes on which Airbus modification 10155 has not 
been embodied: Before exceeding 15,100 FC or 38,900 FH, whichever 
occurs first after first flight of the airplane; or within the 
``grace periods'' defined in paragraph 1.B.(4), ``Accomplishment 
Timescale,'' of Airbus Service Bulletin A300-57-6050, Revision 3, 
dated May 31, 2001; whichever occurs later, modify the angle fitting 
attachment holes of the wing center box by cold expansion, including 
doing a rotating probe inspection for cracking, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A300-57-
6050, Revision 3, dated May 31, 2001. Where paragraph 1.B.(4), 
``Accomplishment Timescale,'' of Airbus Service Bulletin A300-57-
6050, Revision 3, dated May 31, 2001, specifies ``grace periods'' 
relative to the receipt of the service bulletin, count the ``grace 
periods'' from December 19, 2005 (the effective date of AD 2005-23-
08). If any crack is found during any inspection: 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's EASA Design Organization Approval 
(DOA). If approved by the DOA, the approval must include the DOA-
authorized signature.

(i) Internal Lower Angle Fitting (Vertical Face) Web Inspections

    For Group 1 airplanes: Before exceeding the applicable threshold 
specified in figure 1 to paragraph (i) of this AD, or within 12 
months after the effective date of this AD, whichever occurs later, 
do a high frequency eddy current (HFEC) rotating probe inspection 
for cracking of holes H, I, K, L, M, N, U, V, W, X, and Y of the 
internal lower angle fitting web (left-hand and right-hand sides), 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-6049, Revision 8, dated July 4, 2017. Repeat the 
inspection thereafter at intervals not to exceed those specified in 
figure 1 to paragraph (i) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.002

(j) Internal Lower Angle Fitting (Horizontal Face) Inspections

    For Group 1 airplanes: Before exceeding the applicable threshold 
specified in figure 2 to paragraph (j) of this AD, or within 12 
months after the effective date of this AD, whichever occurs later, 
do an HFEC rotating probe inspection for cracking of holes A, B, C, 
D, E, F, G, P, Q, S, and T (adjacent to hole G) of the internal 
lower angle fitting horizontal splicing (left-hand and right-hand 
sides), in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A300-57-6086, Revision 6, dated July 4, 2017. 
Repeat the inspection thereafter at intervals not to exceed those 
specified in figure 2 to paragraph (j) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.003


[[Page 25594]]



(k) Aft Bottom Panel Inspections

    For Group 1 airplanes: Before exceeding the applicable 
thresholds specified in figure 3 to paragraph (k) of this AD, or 
within 12 months after the effective date of this AD, whichever 
occurs later, do an ultrasonic inspection for cracking of the aft 
bottom panel, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A300-57-6086, Revision 6, dated July 4, 
2017. Repeat the inspection thereafter at intervals not to exceed 
those specified in figure 3 to paragraph (k) of this AD.
[GRAPHIC] [TIFF OMITTED] TP04JN18.004

(l) FR47/Rib 1 Junction Area Inspections

    For Group 2 airplanes: Before exceeding the applicable 
thresholds specified in figure 4 to paragraph (l) of this AD, do 
ultrasonic and radiographic inspections for cracking of the FR47/Rib 
1 junction area, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-57-6119, Revision 00, dated April 
25, 2016. Repeat the inspections thereafter at intervals not to 
exceed those specified in figure 4 to paragraph (l) of this AD. 
Count the threshold compliance times from the date on which Airbus 
Service Bulletin A300-57-6113, Revision 00, dated April 25, 2016, 
was embodied on the airplane.
[GRAPHIC] [TIFF OMITTED] TP04JN18.005

(m) Related Investigative and Corrective Actions

    If, during any inspection required by paragraph (i), (j), (k), 
or (l) of this AD, any crack is found: Before further flight, 
accomplish all applicable related investigative and corrective 
actions in accordance with the Accomplishment Instructions of the 
service information specified in paragraphs (m)(1) through (m)(3) of 
this AD, as applicable. Where the service information specified in 
paragraphs (m)(1) through (m)(3) of this AD specifies to contact 
Airbus for instructions, before further flight, obtain instructions 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or EASA; or Airbus's EASA DOA and accomplish those 
instructions accordingly. If approved by the DOA, the approval must 
include the DOA-authorized signature.
    (1) If the inspection was done as specified in paragraph (i) of 
this AD: Airbus Service Bulletin A300-57-6049, Revision 8, dated 
July 4, 2017.
    (2) If the inspection was done as specified in paragraph (j) or 
(k) of this AD: Airbus Service Bulletin A300-57-6086, Revision 6, 
dated July 4, 2017.
    (3) If the inspection was done as specified in paragraph (l) of 
this AD: Airbus Service Bulletin A300-57-6119, Revision 00, dated 
April 25, 2016.

(n) Reporting

    At the applicable time specified in paragraph (n)(1) or (n)(2) 
of this AD: Report the results of the inspections required by 
paragraphs (i), (j), (k), and (l) of this AD to Airbus Service 
Bulletin Reporting Online Application on Airbus World (https://w3.airbus.com/), or submit the results to Airbus in accordance with 
the instructions of the applicable service information specified in 
paragraphs (i), (j), (k), or (l) of this AD. The report must include 
the inspection results, a description of any discrepancies found, 
the

[[Page 25595]]

airplane serial number, and the number of flight cycles and flight 
hours on the airplane.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) 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.

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

    Accomplishment of the action required by paragraph (h) of this 
AD and the initial inspections required by paragraphs (i) and (j), 
and (k) of this AD terminates all requirements of AD 2014-20-18.

(p) Credit for Previous Actions

    This paragraph provides credit for actions specified in 
paragraph (h) of this AD, 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.

(q) 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 (r)(2) 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 corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA 
DOA. If approved by the DOA, the approval must include the DOA-
authorized signature.
    (3) 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 
work-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.
    (4) Required for Compliance (RC): Except as required by 
paragraph (m) of this AD: If any service information contains 
procedures or tests that are identified as RC, those procedures and 
tests must be done to comply with this AD; any procedures or tests 
that are not identified as RC are recommended. Those procedures and 
tests that are not identified as RC may be deviated from using 
accepted methods in accordance with the operator's maintenance or 
inspection program without obtaining approval of an AMOC, provided 
the procedures and tests identified as RC can be done and the 
airplane can be put back in an airworthy condition. Any 
substitutions or changes to procedures or tests identified as RC 
require approval of an AMOC.

(r) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0210, dated October 24, 2017, for related 
information. This MCAI may be found in the AD docket on the internet 
at http://www.regulations.gov by searching for and locating Docket 
No. FAA-2018-0497.
    (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.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 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. 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.

    Issued in Des Moines, Washington, on May 23, 2018.
James Cashdollar,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2018-11822 Filed 6-1-18; 8:45 am]
 BILLING CODE 4910-13-P


