
[Federal Register Volume 82, Number 193 (Friday, October 6, 2017)]
[Proposed Rules]
[Pages 46729-46738]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-21221]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-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 supersede Airworthiness Directive (AD) 2004-03-
07, which applies to certain Airbus Model A320-111, -211, -212, and -
231 series airplanes. AD 2004-03-07 requires repetitive inspections for 
fatigue cracking around the fasteners attaching the pressure panel to 
the flexible bracket at frame (FR) 36, adjacent to the longitudinal 
beams on the left and right sides of the airplane; and repair as 
necessary. Since we issued AD 2004-03-07, additional cracking has been 
found under the longitudinal beams in locations outside of the 
inspection areas required by AD 2004-03-07. This proposed AD would 
retain certain requirements of AD 2004-03-07, expand the applicability, 
and require an inspection of the fastener holes on the pressure panel 
between FR 35 and FR 36 under the longitudinal beam and modification or 
repair as applicable. We are proposing this AD to address the unsafe 
condition on these products.

DATES: We must receive comments on this proposed AD by November 20, 
2017.

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 account.airworth-eas@airbus.com; 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-
0902; 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-2017-0902; 
Product Identifier 2016-NM-188-AD at the beginning of your comments. We 
specifically invite comments on the overall regulatory,

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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

    On January 29, 2004, we issued AD 2004-03-07, Amendment 39-13451 
(69 FR 5907, February 9, 2004) (``AD 2004-03-07''), for certain Airbus 
Model A320-111, -211, -212, and -231 series airplanes. AD 2004-03-07 
was prompted by fatigue tests which revealed cracking around the 
fasteners attaching the pressure panel to the flexible bracket at FR 
36, adjacent to the longitudinal beams on the left and right sides of 
the airplane. Investigation revealed that the damage was caused by high 
loads in this area. AD 2004-03-07 requires repetitive inspections for 
fatigue cracking around the fasteners attaching the pressure panel to 
the flexible bracket at FR 36, adjacent to the longitudinal beams on 
the left and right sides of the airplane; and repair as necessary. AD 
2004-03-07 also provides an optional terminating action for the 
repetitive inspections. We issued AD 2004-03-07 to detect and correct 
fatigue cracking around the fasteners attaching the pressure panel to 
the flexible bracket at the FR 36 adjacent to the longitudinal beams, 
which could result in reduced structural integrity and possible rapid 
decompression of the airplane.
    Since we issued AD 2004-03-07, additional cracks have been found 
under the longitudinal beams at locations that are not included in the 
inspection area required by AD 2004-03-07. Fatigue and damage tolerance 
analyses were performed and the results indicated that all the holes in 
the pressure panel above the longitudinal beams have to be cold worked.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2016-0206, dated October 13, 2016; corrected 
October 14, 2016 (referred to after this as the Mandatory Continuing 
Airworthiness Information, or ``the MCAI''), to correct an unsafe 
condition for certain Airbus Model A318 and Model A319 series 
airplanes, Model A320-211, -212, -214, -231, -232, and -233 airplanes, 
and Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    During fatigue tests, cracks were found around the fasteners 
connecting the pressure panel with the flexible bracket at fuselage 
frame (FR) 36, adjacent to the longitudinal beams on left-hand (LH) 
and right-hand (RH) sides.
    This condition, if not detected and corrected, could impair the 
structural integrity of the aeroplane.
    To address this unsafe condition, DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued [French] 
AD 2000-531-155(B) [which corresponds with FAA AD 2004-03-07] to 
require repetitive inspections of the longitudinal beams of the FR 
36 pressure panel and, depending on findings, the accomplishment of 
a repair.
    Since that [French] AD was issued, additional cracks have been 
found under the beams, but in locations not covered by the required 
inspections. Fatigue and damage tolerance analyses were performed, 
the results of which indicated that all the holes in the pressure 
panel above all the longitudinal beams have to be cold worked.
    For the reasons described above, this [EASA] AD retains the 
requirements of DGAC France AD 2000-531-155(B), which is superseded, 
extends the applicability to all A320 family aeroplanes and requires 
[a special detailed inspection of the fastener holes on the pressure 
panel between FR35 and FR36 under the longitudinal beam and] 
modification [or repair] of all the affected holes.
    This [EASA] AD is republished to correct the number of the 
superseded DGAC 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-
0902.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-53-1264, Revision 01, dated 
July 4, 2016. The service information describes procedures for a 
special detailed inspection (rotating probe) for cracking of the 
fastener holes on the pressure panel between FR 35 and FR 36 under the 
longitudinal beam and repair of any crack.
    Airbus has also issued Service Bulletin A320-53-1240, Revision 01, 
dated April 4, 2016, which describes procedures for modifying the 
pressure panel above the left and right longitudinal beams, including 
related investigative action (e.g., high frequency eddy current 
(rototest) inspection of all the removed fastener holes) and corrective 
actions (e.g., repair), by cold working the attachment holes under the 
longitudinal beam at FR 36 for airplanes on which no cracking was 
found.
    In addition, Airbus issued Service Bulletin A320-53-1263, Revision 
01, dated February 29, 2016, which describes procedures for modifying 
the pressure panel above the left and right longitudinal beams, 
including related investigative actions (e.g., eddy current rotating 
probe inspection of the fastener holes) and corrective actions (e.g., 
repair), by adding a doubler and a filler, and cold expansion of the 
holes under the longitudinal beam at FR 36 for airplanes on which 
cracking was found.
    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 these 
same type designs.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI specifies that operators can calculate revised thresholds 
for Model A319 and A320 series airplanes with sharklets installed 
(Airbus Service Bulletin A320-57-1193). This proposed AD does not 
include those calculations because the calculations could result in 
different inspection thresholds for each individual airplane. However, 
under the provisions of paragraph (o)(1) of this AD, we will consider 
requests for approval of alternative compliance times.

Costs of Compliance

    We estimate that this proposed AD affects 737 airplanes of U.S. 
registry.
    We estimate the following costs to comply with this proposed AD:

[[Page 46731]]



                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                 Cost on U.S.
             Action                     Labor cost          Parts cost     Cost per product        operators
----------------------------------------------------------------------------------------------------------------
Inspection [Retained from AD     Up to 2 work-hours x                 $0  Up to $170 per      Up to $125,290 per
 2004-03-07].                     $85 per hour = $170                      inspection cycle.   inspection cycle.
                                  per inspection cycle.
Inspection [new proposed         13 work-hours x $85 per               0  $1,105............  $814,385.
 requirement].                    hour = $1,105.
----------------------------------------------------------------------------------------------------------------

    We estimate the following costs to do any necessary modifications 
that would be required based on the results of the proposed inspection. 
We have no way of determining the number of aircraft that might need 
these modifications:

                                               On-Condition Costs
----------------------------------------------------------------------------------------------------------------
               Action                         Labor cost                Parts cost           Cost per product
----------------------------------------------------------------------------------------------------------------
Modification.......................  Up to 213 work-hours x $85   Up to $8,510..........  Up to $26,615.
                                      per hour = $18,105.
Reporting..........................  1 work-hour x $85 per hour   $0....................  $85.
                                      = $85.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that would enable us to provide 
a cost estimate for the on-condition repairs specified in the service 
information.

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 removing Airworthiness Directive (AD) 
2004-03-07, Amendment 39-13451 (69 FR 5907, February 9, 2004), and 
adding the following new AD:

Airbus: Docket No. FAA-2017-0902; Product Identifier 2016-NM-188-AD.

(a) Comments Due Date

    We must receive comments by November 20, 2017.

(b) Affected ADs

    This AD replaces AD 2004-03-07, Amendment 39-13451 (69 FR 5907, 
February 9, 2004) (``AD 2004-03-07'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, 
except for airplanes on which Airbus Modification 151574 was 
embodied in production.
    (1) Model A318-111, -112, -121, and -122 airplanes.
    (2) Model A319-111, -112, -113, -114, -115, -131, -132, and -133 
airplanes.
    (3) Model A320-211, -212, -214, -231, -232, and -233 airplanes.

[[Page 46732]]

    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by fatigue tests which revealed cracking 
around the fasteners attaching the pressure panel to the flexible 
bracket at frame (FR) 36, adjacent to the longitudinal beams on the 
left and right sides of the airplane. We are issuing this AD to 
detect and correct fatigue cracking around the fasteners attaching 
the pressure panel to the flexible bracket at the FR 36 adjacent to 
the longitudinal beams, which could result in reduced structural 
integrity of the airplane and possible rapid decompression of the 
airplane.

(f) Compliance

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

(g) Retained Inspection and Follow-On Actions, With No Changes

    This paragraph restates the requirements of paragraphs (a) and 
(b) of AD 2004-03-07, with no changes.
    (1) For Model A320-211, -212, and -231 series airplanes having 
serial numbers 0002 through 0107 inclusive, except those airplanes 
on which Airbus Modification 21202/K1432 has been incorporated in 
production, or on which Airbus Service Bulletin A320-53-1029, 
Revision 01, dated April 29, 2002, has been incorporated: Prior to 
the accumulation of 30,000 total flight cycles, do a rotating probe 
inspection on airplanes with a center fuel tank, or a detailed 
inspection on airplanes without a center fuel tank, to detect 
cracking around the fasteners that attach the pressure panel to the 
flexible bracket at FR 36, adjacent to the longitudinal beams on the 
left and right sides of the airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1030, 
Revision 01, dated May 21, 2002.
    (2) If no crack is detected by the inspection required by 
paragraph (g)(1) of this AD, repeat the applicable inspection 
thereafter at intervals not to exceed 6,000 flight cycles for 
airplanes without a center fuel tank, and at intervals not to exceed 
18,000 flight cycles for airplanes with a center fuel tank.

(h) Retained Corrective Actions, With Specific Delegation Approval 
Language

    This paragraph restates the requirements of paragraphs (c) and 
(d) of AD 2004-03-07, with specific delegation approval language.
    (1) If any crack is detected during any inspection required by 
paragraph (g)(1) of this AD, before further flight, repair the 
affected structure by accomplishing all applicable actions in 
accordance with paragraphs 3.B. through 3.E. of the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1030, Revision 01, 
dated May 21, 2002. Repeat the applicable inspection thereafter at 
intervals not to exceed 6,000 flight cycles for airplanes without a 
center fuel tank, and at intervals not to exceed 18,000 flight 
cycles for airplanes with a center fuel tank. For any area where 
cracking is repaired, the repair constitutes terminating action for 
the repetitive inspection of that area.

    Note 1 to paragraph (h)(1) of this AD: Airbus Service Bulletin 
A320-53-1030 references Airbus Service Bulletin A320-53-1029, 
Revision 01, dated April 29, 2002, as an additional source of 
service information for certain repairs.

    (2) If Airbus Service Bulletin A320-53-1030, Revision 01, dated 
May 21, 2002, specifies to contact the manufacturer for appropriate 
action: Before further flight, repair using a method approved in 
accordance with the procedures specified in paragraph (o)(2) of this 
AD.

(i) Retained Optional Terminating Action for Paragraphs (g) and (h) of 
This AD, With Revised Compliance Language

    This paragraph restates the requirements of paragraph (e) of AD 
2004-03-07, with revised compliance language. For Model A320-211, -
212, and -231 series airplanes having serial numbers 0002 through 
0107 inclusive, except those airplanes on which Airbus Modification 
21202/K1432 has been incorporated in production, or Airbus Service 
Bulletin A320-53-1029, Revision 01, dated April 29, 2002: 
Modification, before the effective date of this AD, of the structure 
around the fasteners that attach the pressure panel to the flexible 
bracket at FR 36, adjacent to the longitudinal beams on the left and 
right sides of the airplane, by accomplishing all applicable actions 
in accordance with paragraphs 3.A. through 3.E. of the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1029, 
Revision 01, dated April 29, 2002, constitutes terminating action 
for the actions required by paragraphs (g) and (h) of this AD.

(j) New Requirement of This AD: Inspection

    For all airplanes, except for airplanes identified in paragraph 
(l) of this AD: At the applicable time specified in table 1 to 
paragraph (j) of this AD, do a special detailed inspection for 
cracking of the fastener holes on the pressure panel between FR 35 
and FR 36 under the longitudinal beam, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1264, 
Revision 01, dated July 4, 2016.
BILLING CODE 4910-13-P

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(k) On-Condition Actions

    (1) If, during any inspection required by paragraph (j) of this 
AD, no cracking is found, or cracking is found that is within the 
limits specified in Airbus Service Bulletin A320-53-1264, Revision 
01, dated July 4, 2016: Before further flight, modify the pressure 
panel above the left and right longitudinal beams, including doing 
all applicable related investigative and corrective actions, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1240, Revision 01, dated April 4, 2016; or Service 
Bulletin A320-53-1263, Revision 01, dated February 29, 2016; as 
applicable. Do all related investigative and corrective actions 
before further flight. Where Airbus Service Bulletin A320-53-1240, 
Revision 01, dated April 4, 2016; and Service Bulletin A320-53-1263, 
Revision 01, dated February 29, 2016; specify to contact Airbus for 
appropriate action: Before further flight, accomplish the repair in 
accordance with the procedures specified in paragraph (o)(2) of this 
AD.
    (2) If, during any inspection required by paragraph (j) of this 
AD, any cracking is found that exceeds the limits specified in 
Airbus Service Bulletin A320-53-1264, Revision 01, dated July 4, 
2016: Do the actions specified in, and at the compliance times 
specified in, paragraphs (k)(2)(i) and (k)(2)(ii) of this AD.
    (i) Before further flight, repair any cracking in accordance 
with the Accomplishment Instructions of Airbus Service Bulletin 
A320-53-1264, Revision 01, dated July 4, 2016. Where Airbus Service 
Bulletin A320-53-1264, Revision 01, dated July 4, 2016, specifies to 
contact Airbus for appropriate action, and specifies that action as 
``RC'' (Required for Compliance): Before further flight, request 
approval of repair instructions using a method approved in 
accordance with the procedures specified in paragraph (o)(2) of this 
AD, and accomplish the repair accordingly within the compliance time 
specified in those instructions. If no compliance time is defined in 
the repair instructions, accomplish the repair before further 
flight.
    (ii) At the times specified in paragraph (k)(2)(ii)(A) or 
(k)(2)(ii)(B) of this AD, as applicable: Report any findings of 
cracking that exceeds the limits specified in Airbus Service 
Bulletin A320-53-1264, Revision 01, dated July 4, 2016, to Airbus 
Customer Services through TechRequest on Airbus World (https://w3.airbus.com/) by selecting Engineering Domain and ATA 57-10.
    (A) If the inspection was done on or after the effective date of 
this AD: Report within 90 days after that inspection.
    (B) If the inspection was done before the effective date of this 
AD: Report within 90 days after the effective date of this AD.

(l) Actions for Certain Airplanes

    For Model A319 and Model A320 series airplanes on which the 
actions specified in Airbus Service Bulletin A320-57-1193 have been 
embodied and the airplane has accumulated 33,000 flight cycles or 
66,000 flight hours or more since the airplane's first flight on the 
effective date of this AD: Within 30 days after the effective date 
of this AD, contact the Manager, International Section, Transport 
Standards Branch FAA; or the EASA; or Airbus's EASA DOA for approved 
repair instructions and within the compliance time specified in 
those instructions, accomplish the repair accordingly. If no 
compliance time is defined in the repair instructions, accomplish 
the repair before the next flight.

(m) Terminating Action for Repetitive Inspections Required by Paragraph 
(g)(2) of This AD

    (1) Modification of an airplane as specified in paragraph 
(m)(1)(i), (m)(1)(ii), or (m)(1)(iii) of this AD constitutes 
terminating action for the repetitive inspection required by 
paragraph (g)(2) of this AD for that airplane only.
    (i) Modification of an airplane as required by paragraph (k)(1) 
of this AD.
    (ii) Modification of an airplane prior to the effective date of 
this AD, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1240, dated March 19, 2015; or 
Airbus Service Bulletin A320-53-1263, dated March 19, 2015; as 
applicable.
    (iii) Modification of an airplane using instructions obtained in 
accordance with the procedures specified in paragraph (o)(2) of this 
AD.
    (2) Repair of an airplane as required by paragraph (k)(2) of 
this AD constitutes terminating action for the repetitive 
inspections required by paragraph (g)(2) of this AD for that 
airplane, unless specified otherwise in the repair instructions 
approved by the Manager, International Section, Transport Standards 
Branch, FAA; or the EASA; or Airbus's EASA DOA.

(n) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraphs (g) and (h)(1) of this AD, if those actions were 
performed before March 15, 2004 (the effective date of AD 2004-03-
07) using Airbus Service Bulletin A320-53-1030, dated January 5, 
2000; or Airbus Service Bulletin A320-53-1029, dated January 5, 
2000.
    (2) This paragraph provides credit for actions required by 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A320-53-
1264, dated March 19, 2015.
    (3) This paragraph provides credit for actions required by 
paragraph (k)(1) of this AD, if those actions were performed before 
the effective date of this AD using Airbus Service Bulletin A320-53-
1240, dated March 19, 2015; or Airbus Service Bulletin A320-53-1263, 
dated March 19, 2015; for that airplane only.

(o) 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 Branch, send it to the attention of 
the person identified paragraph (p)(2) of this AD. Information may 
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office.
    (2) Contacting the Manufacturer: 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 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.
    (3) Required for Compliance (RC): Except as required by 
paragraph (k)(2)(i) 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 5 
minutes 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 AD 2016-0206, dated October 13, 2016; corrected October 
14, 2016; 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-2017-0902.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW.,

[[Page 46738]]

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 account.airworth-eas@airbus.com; 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 September 21, 2017.
Dionne Palermo,
Acting Director, System Oversight Branch, Aircraft Certification 
Service.
[FR Doc. 2017-21221 Filed 10-5-17; 8:45 am]
 BILLING CODE 4910-13-P


