[Federal Register Volume 82, Number 238 (Wednesday, December 13, 2017)]
[Proposed Rules]
[Pages 58566-58572]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-26622]


 ========================================================================
 Proposed Rules
                                                 Federal Register
 ________________________________________________________________________
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 This section of the FEDERAL REGISTER contains notices to the public of 
 the proposed issuance of rules and regulations. The purpose of these 
 notices is to give interested persons an opportunity to participate in 
 the rule making prior to the adoption of the final rules.
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 

  Federal Register / Vol. 82, No. 238 / Wednesday, December 13, 2017 / 
Proposed Rules  

[[Page 58566]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-1102; Product Identifier 2017-NM-078-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2016-01-
11, which applies to certain Airbus Model A320-211, -212, and -231 
airplanes. AD 2016-01-11 requires repetitive inspections for cracking 
of the radius of the front spar vertical stringers and the horizontal 
floor beam on frame 36, repetitive inspections for cracking of the 
fastener holes of the front spar vertical stringers on frame 36, and 
repair if necessary. Since we issued AD 2016-01-11, we received a 
report that, during a center fuselage certification full scale fatigue 
test, cracks were found on the front vertical stringer at a certain 
frame. This proposed AD would add new thresholds and intervals for the 
repetitive inspections; would require, for certain airplanes, a 
modification of the center wing box area; and would expand the 
applicability. We are proposing this AD to address the unsafe condition 
on these products.

DATES: We must receive comments on this proposed AD by January 29, 
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, 
Airworthiness Office-EIAS, 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 referenced service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

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-2017-
1102; 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 proposed AD, 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: Sanjay Ralhan, Aerospace Engineer, 
International Section, Transport Standards Branch, FAA, 1601 Lind 
Avenue SW, Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.

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-2017-1102; 
Product Identifier 2017-NM-078-AD'' at the beginning of your comments. 
We specifically invite comments on the overall regulatory, economic, 
environmental, and energy aspects of this proposed AD. We will consider 
all comments received by the closing date and may amend this proposed 
AD 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 proposed AD.

Discussion

    Fatigue damage can occur locally, in small areas or structural 
design details, or globally, in widespread areas. Multiple-site damage 
is widespread damage that occurs in a large structural element such as 
a single rivet line of a lap splice joining two large skin panels. 
Widespread damage can also occur in multiple elements such as adjacent 
frames or stringers. Multiple-site damage and multiple-element damage 
cracks are typically too small initially to be reliably detected with 
normal inspection methods. Without intervention, these cracks will 
grow, and eventually compromise the structural integrity of the 
airplane. This condition is known as widespread fatigue damage (WFD). 
It is associated with general degradation of large areas of structure 
with similar structural details and stress levels. As an airplane ages, 
WFD will likely occur, and will certainly occur if the airplane is 
operated long enough without any intervention.
    The FAA's WFD final rule (75 FR 69746, November 15, 2010) became 
effective on January 14, 2011. The WFD rule requires certain actions to 
prevent structural failure due to WFD throughout the operational life 
of certain existing transport category airplanes and all of these 
airplanes that will be certificated in the future. For existing and 
future airplanes subject to the WFD rule, the rule requires that DAHs 
establish a limit of validity (LOV) of the engineering data that 
support the structural maintenance program. Operators affected by the 
WFD rule may not fly an airplane beyond its LOV, unless an extended LOV 
is approved.
    The WFD rule (75 FR 69746, November 15, 2010) does not require 
identifying and developing maintenance actions if the DAHs can show 
that such actions are not necessary to prevent WFD before the airplane 
reaches the LOV. Many LOVs, however, do depend on accomplishment of 
future maintenance actions. As stated in the WFD rule, any maintenance 
actions

[[Page 58567]]

necessary to reach the LOV will be mandated by airworthiness directives 
through separate rulemaking actions.
    In the context of WFD, this action is necessary to enable DAHs to 
propose LOVs that allow operators the longest operational lives for 
their airplanes, and still ensure that WFD will not occur. This 
approach allows for an implementation strategy that provides 
flexibility to DAHs in determining the timing of service information 
development (with FAA approval), while providing operators with 
certainty regarding the LOV applicable to their airplanes.
    We issued AD 2016-01-11, Amendment 39-18370 (81 FR 3316, January 
21, 2016) (``AD 2016-01-11''), for certain Airbus Model A320-211, -212, 
and -231 airplanes. AD 2016-01-11 was prompted by reports that indicate 
new repetitive inspections having new thresholds and intervals were 
needed and that additional work was needed to accomplish the 
inspections on airplanes on which a previous modification has been 
accomplished. AD 2016-01-11 requires repetitive high frequency eddy 
current (HFEC) inspections for cracking of the radius of the front spar 
vertical stringers and the horizontal floor beam on frame 36, 
repetitive rototest inspections for cracking of the fastener holes of 
the front spar vertical stringers on frame 36, and repair if necessary. 
We issued AD 2016-01-11 to detect and correct fatigue cracking of the 
front spar vertical stringers on the wings, which could result in the 
reduced structural integrity of the airplane.
    Since we issued AD 2016-01-11, the European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Union, has issued EASA Airworthiness Directive 2017-0099, 
dated June 8, 2017 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus Model A318 series airplanes; Model A319 
series airplanes; Model A320-211, -212, -214, -231, -232, and -233 
airplanes; and Model A321 series airplanes. The MCAI states:

    During centre fuselage certification full scale fatigue test, 
cracks were found on the front vertical stringer at frame (FR) 36. 
Analysis of these findings indicated that a number of in-service 
aeroplanes could be similarly affected.
    This condition, if not detected and corrected, could lead to 
crack propagation and consequent deterioration of the structural 
integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued Airbus 
Service Bulletin (SB) A320-57-1016 to provide inspection 
instructions, and, consequently, [Directorate General for Civil 
Aviation] DGAC France issued AD 97-311-105 [which corresponds to FAA 
AD 98-18-26, Amendment 39-10742 (63 FR 47423, September 8, 1998)] to 
require those repetitive [high frequency eddy current (HFEC)] 
inspections [for cracking]. At the same time, modification in 
accordance with Airbus SB A320-57-1017 was introduced as (optional) 
terminating action for the repetitive inspections * * *.
    After that [DGAC] AD was issued, and following new analysis, 
modification per Airbus SB A320-57-1017 was no longer considered to 
be terminating action for the repetitive inspections as required by 
DGAC France AD 97-311-105. Aeroplanes with [manufacturer serial 
number] MSN 0080 up to MSN 0155 inclusive were delivered with the 
addition of a 5 [millimeter] mm thick light alloy shim under the 
heads of 2 fasteners at the top end of the front spar vertical 
stringers (Airbus mod 21290P1546, which is the production line 
equivalent to in-service modification through Airbus SB A320-57-
1017). Aeroplanes with MSN 0156 or higher are delivered with 
vertical stiffeners of the forward wing spar upper end with 
stiffener cap thickness increased from 4 to 6 mm (Airbus mod 
21290P1547).
    Prompted by these findings, Airbus issued SB A320-57-1178 
Revision 01 to introduce new repetitive inspections and, 
consequently, EASA issued AD 2014-0069 [which corresponds to FAA AD 
2016-01-11], superseding DGAC France AD 97-311-105 to require the 
new repetitive inspections, and, depending on findings, 
accomplishment of applicable corrective action(s).
    Since AD 2014-0069 was issued, further investigations in the 
frame of the Widespread Fatigue Damage (WFD) campaign identified 
that some repetitive inspection thresholds and intervals have to be 
revised or introduced, and a new terminating action modification has 
been designed.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0069, which is superseded, revises and 
introduces thresholds and intervals for the repetitive inspections, 
and expands the Applicability.

    Required actions also include reporting. Although this proposed AD 
does not explicitly restate the requirements of AD 2016-01-11, this 
proposed AD would retain certain requirements of AD 2016-01-11. Those 
requirements are referenced in the service information identified below 
in ``Related Service Information under 1 CFR part 51,'' which is 
referenced in paragraph (i)(1) of this proposed AD. 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-2017-1102.

Related Service Information Under 1 CFR Part 51

    Airbus has issued the following service information:
     Service Bulletin A320-57-1178, Revision 03, dated November 
29, 2016; excluding Appendixes 01 and 04, and including Appendix 03, 
all dated November 29, 2016. Appendix 02 does not exist. The service 
information describes procedures for a rototest inspection for cracking 
of the radius of the front spar vertical stringers on frame 36, a HFEC 
for cracking of the horizontal floor beam, and an HFEC inspection for 
cracking of the fastener holes of the front spar vertical stringers.
     Service Bulletin A320-57-1200, dated November 20, 2015. 
The service information describes procedures for modifying the center 
wing box area, which includes related investigative and corrective 
actions. Related investigative actions include an HFEC inspection on 
the radius of the rib flanges, a rototest inspection of the fastener 
holes, detailed and high frequency eddy current inspections for 
cracking on the cut edges, detailed and rototest inspections on all 
open fastener holes and an inspection to determine if secondary 
structure brackets are installed. Corrective action includes reworking 
the secondary structure bracket and repair.
    This service information is reasonably available because the 
interested parties have access to it through their normal course of 
business or by the means identified in the ADDRESSES section.

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.

Explanation of Compliance Time

    The compliance time for the replacement specified in this proposed 
AD for addressing WFD was established to ensure that discrepant 
structure is replaced before WFD develops in airplanes. Standard 
inspection techniques cannot be relied on to detect WFD before it 
becomes a hazard to flight. We will not grant any extensions of the 
compliance time to complete any AD-mandated service bulletin related to 
WFD without extensive new data that would substantiate and clearly 
warrant such an extension.

[[Page 58568]]

Costs of Compliance

    We estimate that this proposed AD affects 815 airplanes of U.S. 
registry.
    The actions required by AD 2016-01-11, take about 24 work-hours per 
product, at an average labor rate of $85 per work-hour. Based on these 
figures, the estimated cost of the actions that are required by AD 
2016-01-11 is $2,040 per product.
    We also estimate that it would take about 25 work-hours per product 
to comply with the basic requirements of this proposed AD and 1 work-
hour for reporting. The average labor rate is $85 per work-hour. 
Required parts would cost about $180 per product. Based on these 
figures, we estimate the cost of this proposed AD on U.S. operators to 
be $1,947,850, or $2,390 per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the repair of cracking 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 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 removing Airworthiness Directive (AD) 
2016-01-11, Amendment 39-18370 (81 FR 3316, January 21, 2016), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-1102; Product Identifier 2017-NM-078-AD.

(a) Comments Due Date

    We must receive comments by January 29, 2018.

(b) Affected ADs

    This AD replaces AD 2016-01-11, Amendment 39-18370 (81 FR 3316, 
January 21, 2016) (``AD 2016-01-11'').

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
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; certificated in any category; all 
manufacturer serial numbers, except airplanes specified in 
paragraphs (c)(1) and (c)(2) of this AD.
    (1) Model A319 and A320 series airplanes on which Airbus 
Modification (Mod) 160000 (structural reinforcement for sharklet 
installation) has been embodied in production.
    (2) Model A321 series airplanes on which Airbus Modification 
(Mod) 160021 (structural reinforcement for sharklet installation) 
has been embodied in production.

(d) Subject

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

(e) Reason

    This AD was prompted by a report that, during a center fuselage 
certification full scale fatigue test, cracks were found on the 
front vertical stringer at frame (FR) 36. We are issuing this AD to 
detect and correct fatigue cracking of the front spar vertical 
stringers on the wings, which could result in the reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Definition of Airplane Configurations

    For the purposes of this AD, airplane configurations are defined 
in table 1 to paragraphs (g), (h), (i)(1), and (j) of this AD and 
table 2 to paragraphs (g) and (i)(1) of this AD.
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[[Page 58569]]

[GRAPHIC] [TIFF OMITTED] TP13DE17.000

(h) Actions Required for Previously Inspected Airplanes

    For Configuration 1, 2, or 3 airplanes, as identified in table 1 
to paragraphs (g), (h), (i)(1), and (j) of this AD, on which the 
inspections specified in Airbus Service Bulletin A320-57-1178, dated 
October 29, 2013, have been accomplished before the effective date 
of this AD; but the additional work specified in Airbus Service 
Bulletin A320-57-1178, Revision 01, dated May 28, 2014, including 
Appendix 01, dated May 28, 2014, has not been accomplished before 
the effective date of this AD: Before accomplishing the initial 
inspection required by paragraph (i)(1) of this AD, contact the 
Manager, International Section, Transport Standards Branch, FAA; or 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA) for further instructions and accomplish 
those instructions accordingly.

(i) Repetitive Inspections

    (1) Within the compliance time defined in table 3 to paragraph 
(i)(1) of this AD, as applicable to airplane configuration as 
identified in table 1 to paragraphs (g), (h),

[[Page 58570]]

(i)(1), and (j) of this AD and table 2 to paragraphs (g) and (i)(1) 
of this AD, accomplish a special detailed inspection (SDI) for 
cracking of the radius of the front spar vertical stringers and the 
horizontal floor beam and the fastener holes on frame 36, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1178, Revision 03, dated November 29, 2016.
[GRAPHIC] [TIFF OMITTED] TP13DE17.001

    (2) If no cracking is found during any inspection required by 
paragraph (i)(1) of this AD, repeat the inspection required by 
paragraph (i)(1) of this AD thereafter at intervals not to exceed 
the inspection interval values defined in table 4 to paragraphs 
(i)(2) and (l) of this AD, except as provided by paragraph (l) of 
this AD.

[[Page 58571]]

[GRAPHIC] [TIFF OMITTED] TP13DE17.002

(j) Modification

    For A320 series airplanes, Configuration 1, 2, or 3 as 
identified in table 1 to paragraphs (g), (h), (i)(1), and (j) of 
this AD: Within the compliance time defined in table 5 to paragraph 
(j) of this AD, as applicable, modify the center wing box area, 
including doing all applicable related investigative and corrective 
actions, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-57-1200, dated November 20, 2015, 
except as required by paragraph (k) of this AD. Do all applicable 
related investigative and corrective actions before further flight.
[GRAPHIC] [TIFF OMITTED] TP13DE17.003

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(k) Corrective Action

    If any crack is found during any inspection required by this AD: 
Before further flight, repair using a method approved by the 
Manager, International Section, Transport Standards Branch, FAA; or 
the EASA; or Airbus's EASA DOA. If approved by the DOA, the approval 
must include the DOA-authorized signature. Where Airbus Service 
Bulletin A320-57-1178, Revision 03, dated November 29, 2016; and 
Airbus Service Bulletin A320-57-1200, dated November 20, 2015; 
specify to contact Airbus for appropriate action, and specifies that 
action as ``RC'' (Required for Compliance), accomplish corrective 
actions in accordance with this paragraph.

(l) Previous Repairs

    For airplanes that have been repaired in the inspection area 
specified in paragraph (i)(1) of this AD before the effective date 
of this AD, using a method approved by the

[[Page 58572]]

Manager, International Section, Transport Standards Branch, FAA; or 
the EASA; or Airbus's EASA DOA: Accomplish repetitive SDIs within 
the compliance time defined in those repair instructions for 
repetitive SDIs. If no compliance time is identified in the repair 
instructions for repetitive SDIs, accomplish the repetitive SDIs 
required by paragraph (i)(2) of this AD at the compliance times 
defined in table 4 to paragraphs (i)(2) and (l) of this AD.

(m) No Terminating Action

    Modification or repair of an airplane, as specified in paragraph 
(j) or (k) of this AD, does not constitute terminating action for 
the repetitive inspections required by this AD, unless it is 
specified otherwise in a repair method approved by the Manager, 
International Section, Transport Standards Branch, FAA; or the EASA; 
or Airbus's EASA DOA.

(n) Reporting Requirement

    Submit a report of the findings (both positive and negative) of 
the inspections required by paragraphs (i) and (j) of this AD to 
``Airbus Service Bulletin Reporting Online Application'' on Airbus 
World (https://w3.airbus.com/), at the applicable time specified in 
paragraph (n)(1) or (n)(2) of this AD.
    (1) If the inspection was done on or after the effective date of 
this AD: Report within 30 days after that inspection.
    (2) If the inspection was done before the effective date of this 
AD: Report within 30 days after the effective date of this AD.

(o) Other FAA AD Provisions

    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, FAA, has the 
authority to approve AMOCs for this AD, if requested using the 
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19, 
send your request to your principal inspector or local Flight 
Standards District Office, as appropriate. If sending information 
directly to the manager of the International Section, send it to the 
attention of the person identified in paragraph (p)(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: As of the effective date of 
this AD, for any requirement in this AD to obtain corrective actions 
from a manufacturer, the action must be accomplished using a method 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as specified in 
paragraph (k) 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.
    (4) Reporting Requirements: 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 [XX] 
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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2017-0099, dated June 8, 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-2017-1102.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 
425-227-1405; fax 425-227-1149.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office-EIAS, 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, 1601 Lind Avenue SW, Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.

    Issued in Renton, Washington, on November 22, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-26622 Filed 12-12-17; 8:45 am]
 BILLING CODE 4910-13-P