Document ID: FAA-2018-0795-0001
Agency: faa
Document Type: Proposed Rule
Title: Airworthiness Directives: Airbus SAS Airplanes
Posted Date: 2018-09-17T04:00Z

[Federal Register Volume 83, Number 180 (Monday, September 17, 2018)]
[Proposed Rules]
[Pages 46905-46909]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-19932]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2018-0795; Product Identifier 2018-NM-076-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus SAS 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) 2014-20-
04, which applies to all Airbus SAS Model A318 series airplanes; Airbus 
SAS Model A319 series airplanes; Airbus SAS Model A320-111, -211, -212, 
-214, -231, -232, and -233 airplanes; and Airbus SAS Model A321-111, -
112, -131, -211, -212, -213, -231, and -232 airplanes. AD 2014-20-04 
requires repetitive inspections for cracking of the four titanium 
angles between the belly fairing and the keel beam side panel, an 
inspection for cracking of the open holes if any cracking is found in 
the titanium angles, and repair or replacement if necessary. Since we 
issued AD 2014-20-04, we have determined that additional work is 
necessary for certain airplanes. This proposed AD would continue to 
require repetitive inspections for cracking of the four titanium angles 
between the belly fairing and the keel beam side panel, an inspection 
for cracking of the open holes if any cracking is found in the titanium 
angles, and repair or replacement if necessary. This proposed AD would 
also revise the applicability by adding Model A320-216 airplanes. This 
proposed AD would also require a detailed inspection for and 
replacement of certain rivets (including a rotating probe test for 
cracks in the open holes), 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 November 1, 
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--EIAS, Rond-Point Emile Dewoitine No: 2, 
31700 Blagnac Cedex, France; phone: +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, 2200 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-
0795; or in person at Docket Operations between 9 a.m. and 5 p.m., 
Monday through Friday, except Federal holidays. The AD docket contains 
this NPRM, the regulatory evaluation, any comments received, and other 
information. The street address for Docket Operations (phone: 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, 2200 South 
216th St., Des Moines, WA 98198; phone and fax 206-231-3223.

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-2018-0795; 
Product Identifier 2018-NM-076-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

    We issued AD 2014-20-04, Amendment 39-17977 (79 FR 59636,

[[Page 46906]]

October 3, 2014) (``AD 2014-20-04''), for all Airbus SAS Model A318 
series airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS 
Model A320-211, -212, -214, -231, -232, and -233 airplanes; and Airbus 
SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. AD 2014-20-04 requires repetitive inspections for cracking 
of the four titanium angles between the belly fairing and the keel beam 
side panel, an inspection for cracking of the open holes if any 
cracking is found in the titanium angles, and repair or replacement if 
necessary. AD 2014-20-04 resulted from reports of cracks at the lower 
riveting of the four titanium angles that connect the belly fairing to 
the keel beam side panels on both sides of the fuselage. We issued AD 
2014-20-04 to address cracking of the titanium angles that connect the 
belly fairing to the keel beam side panels on both sides of the 
fuselage, which could affect the structural integrity of the airplane.

Actions Since AD 2014-20-04 Was Issued

    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2018-0091, dated April 20, 2018 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus SAS Model A318 series 
airplanes; Airbus SAS Model A319 series airplanes; Airbus SAS Model 
A320-211, -212, -214, -216, -231, -232, and -233 airplanes; and Airbus 
SAS Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes. The MCAI states:

    During the fatigue test campaign of the A320 family type design, 
cracks were found at the lower riveting of the four titanium angles 
which connect the belly fairing to the keel beam side panels between 
frames FR40 and FR42, on both sides of the fuselage.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    To address this potential unsafe condition, Airbus issued 
Service Bulletin (SB) A320-53-1014, and DGAC [Direction 
G[eacute]n[eacute]rale de l'Aviation Civile] France issued AD 92-
201-030 [which corresponds to FAA AD 94-12-03, Amendment 39-8930 (59 
FR 28763, June 3, 1994)(``AD 94-12-03'')] to require reinforcement 
of the belly fairing structure.
    Following new investigation which showed that these measures 
addressed only part of the unsafe condition, Airbus published SB 
A320-53-1259 and EASA issued AD 2013-0122 [which corresponds to FAA 
AD 2014-20-04], retaining the requirements of DGAC France AD 92-201-
030, which was superseded, and requiring repetitive detailed 
inspections (DET) of the affected titanium angles and, depending on 
findings, repair or replacement of parts.
    After that [EASA] AD was issued, Airbus published Revision 
(Rev.) 01 and Rev. 02 of SB A320-53-1259. [Airbus SB A320-53-1259] 
Rev. 02 provided incorrect instructions to use Part Number (P/N) 
EN6081D4 rivets for the titanium angles installation, instead of P/N 
EN6081D5 rivets. Consequently, Airbus SB A320-53-1259 was updated 
(now at Rev. 03) including reference to the proper rivets.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2013-0122, which is superseded, and requires 
additional work [a detailed inspection for and replacement of 
certain rivets, and applicable corrective actions] for aeroplanes on 
which Airbus SB A320-53-1259 at Rev. 02 was embodied.

    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-
0795.

Model A320-216 Airplanes

    The Airbus SAS Model A320-216 was type certificated on December 19, 
2016. Before that date, any EASA ADs that affected Model A320-216 
airplanes were included on the Required Airworthiness Actions List 
(RAAL). One or more Model A320-216 airplanes have subsequently been 
placed on the U.S. Register, and will now be included in FAA AD 
actions. For Model A320-216 airplanes, the requirements that correspond 
to AD 2014-20-04 were mandated by the MCAI via the RAAL. Although that 
RAAL requirement is still in effect, for continuity and clarity we have 
identified Model A320-216 airplanes in paragraph (c) of this AD; the 
restated requirements of paragraphs (h) through (n) in this proposed AD 
would therefore apply to those airplanes.

Related Service Information Under 1 CFR Part 51

    Airbus SAS has issued Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017. This service information describes procedures 
for repetitive inspections for cracking of the four titanium angles 
between the belly fairing and the keel beam side panel, an inspection 
for cracking of the open holes if any cracking is found in the titanium 
angles, repair or replacement if necessary, and a detailed inspection 
for and replacement of certain rivets (including a rotating probe test 
for cracks in the open holes).
    Airbus also issued Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994. This service information describes procedures for 
reinforcement (modification) of the belly fairing structure.
    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

    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 the relevant information and determined the unsafe 
condition described previously is likely to exist or develop on other 
products of the same type design.

Proposed Requirements of This NPRM

    This proposed AD would retain all requirements of AD 2014-20-04. 
This proposed AD would also require accomplishing the actions specified 
in the service information described previously.

Costs of Compliance

    We estimate that this proposed AD affects 1,250 airplanes of U.S. 
registry. We estimate the following costs to comply with this proposed 
AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
           Labor cost              Parts cost            Cost per product              Cost on U.S. operators
----------------------------------------------------------------------------------------------------------------
295 work-hours x $85 per hour =          $1,045  $26,120.........................  $32,650,000.
 $25,075 (Old actions of AD
 2014-20-04).
Up to 168 work-hours x $85 per                0  Up to $14,280...................  Up to $17,850,000.
 hour = Up to $14,280 (New
 actions of this AD).
----------------------------------------------------------------------------------------------------------------

[[Page 46907]]

    We estimate the following costs to do any necessary replacement 
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 
this replacement:

                 Estimated Costs of On-Condition Actions
------------------------------------------------------------------------
                                                             Cost per
              Labor cost                  Parts cost *       product
------------------------------------------------------------------------
168 work-hours x $85 per hour =                     $0          $14,280
 $14,280..............................
------------------------------------------------------------------------
* We have received no definitive data that would enable us to provide
  cost estimates for the on-condition parts costs.

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) 
2014-20-04, Amendment 39-17977 (79 FR 59636, October 3, 2014), and 
adding the following new AD:

Airbus SAS: Docket No. FAA-2018-0795; Product Identifier 2018-NM-
076-AD.

(a) Comments Due Date

    We must receive comments by November 1, 2018.

(b) Affected ADs

    This AD replaces AD 2014-20-04, Amendment 39-17977 (79 FR 59636, 
October 3, 2014) (``AD 2014-20-04'').

(c) Applicability

    This AD applies to the Airbus SAS airplanes specified in 
paragraphs (c)(1), (c)(2), (c)(3), and (c)(4) of this AD, 
certificated in any category, all manufacturer serial numbers.
    (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, -216, -231, -232, and -233 
airplanes.
    (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 reports of cracks at the lower riveting 
of the four titanium angles that connect the belly fairing to the 
keel beam side panels on both sides of the fuselage. We are issuing 
this AD to detect and correct cracking of the titanium angles that 
connect the belly fairing to the keel beam side panels on both sides 
of the fuselage, which could affect the structural integrity of the 
airplane.

(f) Compliance

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

(g) Retained Modification, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2014-20-04, with no changes. For Model A320-111, -211, and -231 
series airplanes, manufacturer serial numbers 003 through 092 
inclusive: Prior to the accumulation of 12,000 total landings on the 
airplane, or within 300 days after January 10, 1994 (the effective 
date of AD 93-24-11, Amendment 39-8760 (58 FR 64875, December 10, 
1993)), whichever occurs later, modify the belly fairing structure, 
in accordance with the Accomplishment Instructions of an Airbus 
service bulletin specified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD. As of the effective date of this AD, use only the Airbus 
service bulletin specified in paragraph (g)(3) of this AD.
    (1) Airbus Industrie Service Bulletin A320-53-1014, dated June 
25, 1992.
    (2) Airbus Industrie Service Bulletin A320-53-1014, Revision 1, 
dated May 26, 1993.
    (3) Airbus Service Bulletin A320-53-1014, Revision 2, dated 
September 1, 1994.

(h) Retained Repetitive Inspection, With Updated Service Information

    This paragraph restates the requirements of paragraph (h) of AD 
2014-20-04, with updated service information. At the latest of the 
compliance times specified in paragraphs (h)(1), (h)(2), and (h)(3) 
of this AD: Do a detailed inspection for cracking of the four 
titanium angles between the belly fairing and the keel beam side 
panel, in accordance with the Accomplishment Instructions of Airbus 
Service Bulletin A320-53-1259, dated November 6, 2012; or Airbus 
Service Bulletin A320-53-1259, Revision 03, dated November 30, 2017. 
After the effective date of this AD only Airbus Service Bulletin 
A320-53-1259, Revision 03, dated November 30, 2017, may be used.

[[Page 46908]]

    (1) Before the accumulation of 30,000 total flight cycles or 
60,000 total flight hours, whichever occurs first after first flight 
of the airplane.
    (2) Within 30,000 flight cycles or 60,000 flight hours, 
whichever occurs first after modification of the airplane as 
required by paragraph (g) of this AD, or after installation of new 
titanium angles, provided that, prior to installation, a rototest 
for cracking on the open holes has been accomplished with no crack 
findings, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-53-1259, dated November 6, 2012; or 
Airbus Service Bulletin A320-53-1259, Revision 03, dated November 
30, 2017. After the effective date of this AD, only Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017, may be 
used.
    (3) Within 3,000 flight cycles or 6,000 flight hours, whichever 
occurs first after the effective date of this AD.

(i) Retained Post-Inspection Actions for No Crack Findings, With 
Updated Service Information

    This paragraph restates the requirements of paragraph (i) of AD 
2014-20-04, with updated service information. If, during any 
inspection required by paragraph (h) of this AD, there is no crack 
finding: Accomplish the actions specified in either paragraph (i)(1) 
or (i)(2) of this AD.
    (1) Repeat the inspection required by paragraph (h) of this AD 
at intervals not to exceed 5,000 flight cycles or 10,000 flight 
hours, whichever occurs first.
    (2) Before further flight after the inspection required by 
paragraph (h) of this AD, remove all inspected titanium angles, 
accomplish a rototest for cracking on the open holes and, provided 
no cracks are found, install new titanium angles, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017. After the effective date 
of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017, may be used.

(j) Retained Post-Inspection Actions for Any Crack Findings, With 
Updated Service Information

    This paragraph restates the requirements of paragraph (j) of AD 
2014-20-04, with updated service information. If, during any 
inspection required by paragraph (h) of this AD, there is any crack 
finding: Before further flight, remove the affected titanium 
angle(s), accomplish a rototest for cracking on the open holes, and, 
provided no cracks are found, install new titanium angles, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After 
the effective date of this AD, only Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, may be used.

(k) Retained Post-Installation Repetitive Inspections, With Updated 
Service Information

    This paragraph restates the requirements of paragraph (k) of AD 
2014-20-04, with updated service information. For airplanes on which 
new titanium angles were installed as specified in paragraph (i)(2) 
or (j) of this AD: Within 30,000 flight cycles or 60,000 flight 
hours, whichever occurs first after the installation, accomplish a 
detailed inspection for cracking of the four titanium angles between 
the belly fairing and the keel beam side panel, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, dated November 6, 2012; or Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017. After the effective date 
of this AD, only Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017, may be used. Repeat the inspection 
thereafter at intervals not to exceed 5,000 flight cycles or 10,000 
flight hours, whichever occurs first.

(l) Retained Post-Inspection Actions for Any Crack Findings During 
Post-Installation Inspections, With Updated Service Information

    This paragraph restates the requirements of paragraph (l) of AD 
2014-20-04, with updated service information. If, during any 
inspection as required by paragraph (k) of this AD, there is any 
crack finding: Before further flight, remove the affected titanium 
angles, accomplish a rototest for cracking on the open holes, and, 
provided no cracks are found, install new titanium angles, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-53-1259, dated November 6, 2012; or Airbus Service 
Bulletin A320-53-1259, Revision 03, dated November 30, 2017. After 
the effective date of this AD, only Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017, may be used.

(m) Retained Corrective Action for Rototest Crack Finding, With Updated 
Contact Information

    This paragraph restates the requirements of paragraph (m) of AD 
2014-20-04, with updated contact information. If, during any 
rototest as required by paragraph (i), (j), or (l) of this AD, any 
crack is found: 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 SAS's EASA Design Organization Approval (DOA). If approved by 
the DOA, the approval must include the DOA-authorized signature.

(n) Retained No Termination Action for Repetitive Inspections, With No 
Changes

    This paragraph restates the requirements of paragraph (n) of AD 
2014-20-04, with no changes. Repair or replacement of parts as 
specified in this AD does not terminate the repetitive inspections 
required by this AD.

(o) New Requirement of This AD: Detailed Inspection for Certain Rivets

    For airplanes previously inspected using the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1259, dated November 
6, 2012: At the earlier of the times specified in paragraphs (o)(1) 
and (o)(2) of this AD, do a detailed inspection of the rivet 
installation in the belly fairing shear walls and the titanium 
angles for part number EN6081D4 series rivets in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1259, 
Revision 03, dated November 30, 2017. A review of the airplane 
maintenance records is acceptable to comply with the requirements 
this paragraph for that airplane, provided it can be determined that 
no titanium angles have been installed on that airplane in 
accordance with the Accomplishment Instructions of Revision 02 of 
Airbus Service Bulletin A320-53-1259, or if only rivets part number 
EN6081D5 have been used to install the titanium angles on that 
airplane.
    (1) Within 2,000 flight cycles or 4,000 flight hours, whichever 
occurs first after the effective date of this AD.
    (2) Before exceeding 5,000 flight cycles or 10,000 flight hours, 
whichever occurs first after accomplishment of the last inspection 
specified in paragraph (h) of this AD.

(p) New Requirements of This AD: Replacement of Certain Rivets

    If any part number EN6081D4 series rivet is found during any 
inspection required by paragraph (o) of this AD, before further 
flight, do the actions specified in paragraphs (p)(1) and (p)(2) of 
this AD.
    (1) Remove the part number EN6081D4 series rivets and do a 
rotating probe test of the open holes for cracks, in accordance with 
the Accomplishment Instructions of Airbus Service Bulletin A320-53-
1259, Revision 03, dated November 30, 2017. If any crack is found 
during any inspection required by this paragraph, before further 
flight, obtain corrective actions approved by the Manager, 
International Section, Transport Standards Branch, FAA; or EASA; or 
Airbus SAS's EASA DOA; and accomplish the corrective actions within 
the compliance time specified therein. If approved by the DOA, the 
approval must include the DOA-authorized signature.
    (2) Replace part number EN6081D4 series rivets with part number 
EN6081D5 series rivets in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1259, Revision 03, 
dated November 30, 2017.

(q) 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 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].
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.

[[Page 46909]]

    (ii) AMOCs approved previously for AD 2014-20-04, Amendment 39-
17977 (79 FR 59636, October 3, 2014), are approved as AMOCs for the 
corresponding provisions of paragraphs (o) and (p) of this AD.
    (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 EASA; or Airbus SAS's EASA DOA. If approved by the 
DOA, the approval must include the DOA-authorized signature.
    (3) Required for Compliance (RC): 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 2018-0091, dated April 20, 2018, 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-2018-0795.
    (2) For more information about this AD, contact Sanjay Ralhan, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; phone and 
fax 206-231-3223.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine 
No: 2, 31700 Blagnac Cedex, France; phone: +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 August 29, 2018.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2018-19932 Filed 9-14-18; 8:45 am]
 BILLING CODE 4910-13-P