```

[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26115-26121]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09119]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-122-AD; 
Amendment 39-18468; AD 2016-07-23]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A318, A319, A320, and A321 series airplanes. This AD was 
prompted by reports of in-flight loss of fixed and hinged main landing 
gear (MLG) fairings, and reports of post-modification MLG fixed fairing 
assemblies that have wear and corrosion. This AD requires, for certain 
airplanes, repetitive replacements of the fixed fairing upper and lower 
attachment studs of both left-hand (LH) and the right-hand (RH) MLG; 
and repetitive inspections for corrosion, wear, fatigue cracking, and 
loose studs of each forward stud assembly of the fixed fairing door 
upper and lower forward attachment of both LH and RH MLG; and 
replacement if necessary. This AD also provides an optional terminating 
modification for the repetitive replacements of the fixed fairing upper 
and lower attachment studs. We are issuing this AD to prevent in-flight 
detachment of an MLG fixed fairing and consequent damage to the 
airplane.

DATES: This AD becomes effective June 6, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of June 6, 2016.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2458; or in person at the Docket Management Facility, U.S. Department 
of Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
    For service information identified in this final rule, 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 Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. 
For information on the availability of this material at the FAA, call 
425-227-1221. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2458.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A318, 
A319, A320, and A321 series airplanes. The NPRM published in the 
Federal Register on July 8, 2015 (80 FR 38992) (``the NPRM''). The NPRM 
was prompted by reports of in-flight loss of fixed and hinged MLG 
fairings, and reports of post-modification MLG fixed fairing assemblies 
that have wear and corrosion. The NPRM proposed to require, for certain 
airplanes, repetitive replacements of the fixed fairing upper and lower 
attachment studs of both the LH and RH MLG; and repetitive inspections 
for corrosion, wear, fatigue cracking, and loose studs of each forward 
stud assembly of the fixed fairing door upper and lower forward 
attachment of both LH and RH MLG; and replacement if necessary. The 
NPRM also proposed an optional terminating modification for the 
repetitive replacements of the fixed fairing upper and lower attachment 
studs. We are issuing this AD to prevent in-flight detachment of an MLG 
fixed fairing and consequent damage to the airplane.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0001R1, dated January 15, 2015 (referred 
to after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A318, A319, A320, and A321 series airplanes. The MCAI states:

    Several occurrences of in-flight loss of main landing gear (MLG) 
fixed and hinged fairings were reported. The majority of reported 
events occurred following scheduled maintenance activities. One 
result of the investigation was that a discrepancy between the 
drawing and the maintenance manuals was discovered. The maintenance 
documents were corrected to prevent mis-rigging of the MLG fixed and 
hinged fairings, which could induce fatigue cracking.
    Airbus issued Service Bulletin (SB) A320-52-1083, providing 
instructions for a one-time inspection of the MLG fixed fairing 
composite insert and the surrounding area, replacement of the 
adjustment studs at the lower forward position and adjustment to the 
new clearance tolerances. That SB was replaced by Airbus SB A320-52-
1100 (mod 27716) introducing a re-designed location stud, rod end 
and location plate at the forward upper and lower leg fixed-fairing

[[Page 26116]]

positions. Subsequently, reports were received of post-mod 27716/
post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion, 
which could also induce cracking.
    This condition, if not detected and corrected, could lead to 
further cases of in-flight detachment of a MLG fixed fairing, 
possibly resulting in injury to persons on the ground and/or damage 
to the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2014-
0096 [http://ad.easa.europa.eu/blob/easa_ad_2014_0096_superseded.pdf/AD_2014-0096_1] to require [for 
certain airplanes] repetitive detailed inspections (DET) of the MLG 
fixed fairings, and, depending on findings, accomplishment of 
applicable corrective actions. That [EASA] AD also prohibited 
installation of certain MLG fixed fairing rod end assemblies and 
studs as replacement parts on aeroplanes incorporating Airbus mod 
27716 in production, or modified in accordance with Airbus SB A320-
52-1100 (any revision) in service.
    Since EASA AD 2014-0096 was issued, Airbus developed an 
alternative inspection programme to meet the AD requirements. In 
addition, a terminating action (mod 155648) was developed, which is 
to be made available for in service aeroplanes through Airbus SB 
A320-52-1165.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0096, which is superseded, and adds an 
optional terminating action for the repetitive inspections. For 
post-mod aeroplanes, i.e., incorporating Airbus mod 155648 in 
production, or modified by Airbus SB A320-52-1165 in service, the 
only remaining requirement is to ensure that pre-mod components are 
no longer installed.
    Prompted by these developments, EASA issued AD * * *, retaining 
the requirements of EASA AD 2014-0096, which was superseded, and 
adding an optional terminating action for the repetitive 
inspections. For post-mod aeroplanes, i.e., incorporating Airbus mod 
155648 in production, or modified by Airbus SB A320-52-1165 in 
service, the only remaining requirement is to ensure that pre-mod 
components are no longer installed.
    Since that [EASA] AD was issued, it was discovered that a 
certain plate support, Part Number (P/N) D5285600620000 as listed in 
Table 3 of the [EASA] AD, remains part of the post SB A320-52-1165 
configuration and is therefore not affected by any prohibition of 
installation--paragraph (11) of the [EASA] AD. In addition, an error 
was detected in Table 1 of the [EASA] AD (missing P/N plate support) 
and paragraph (9) was found to be incorrectly worded.
    For the reasons described above, this [EASA] AD is revised to 
introduce the necessary corrections.

    Required actions also include, for airplanes in Airbus pre-Airbus 
Modification 27716 and pre-Airbus Service Bulletin A320-52-1100 
configuration on which certain components have been installed, 
repetitive replacements of the fixed fairing upper and lower attachment 
studs of both the LH and RH MLG. An optional terminating modification 
also is provided for the repetitive replacements of the fixed fairing 
upper and lower attachment studs.
    The optional terminating modification includes a resonance 
frequency inspection for debonding of the composite insert and 
delamination of the honeycomb area around the insert, and applicable 
corrective actions if necessary; and installation of new studs, rod 
ends, and location plates at the forward upper and lower leg fixed-
fairing positions.
    An additional optional terminating modification, for airplanes in 
pre-Airbus Modification 27716 and pre-Airbus Service Bulletin A320-52-
1100 configuration, includes installation of a locking device, new 
studs, rod ends, and location plates at the forward upper and lower leg 
fixed-fairing positions.
    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-2015-
2458.

Comments

    We gave the public the opportunity to participate in developing 
this AD. The following presents the comments received on the NPRM and 
the FAA's response to each comment.

Request To Revise Applicability in SUMMARY Section of the NPRM

    United Airlines (UAL) requested that we revise the SUMMARY section 
of the NPRM to include Model A320 series airplanes.
    We agree with the commenter's request. The published version of the 
NPRM SUMMARY inadvertently did not include Model A320 series airplanes. 
We have revised the SUMMARY section of this final rule accordingly.

Request To Revise Inspection Findings

    UAL requested that we revise paragraphs (i), (k), and (m) of the 
proposed AD, by replacing the term ``fatigue'' with ``deformation.'' 
UAL stated that the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, dated February 4, 2014, do not provide any 
specific method for doing a detailed inspection for indications of 
fatigue.
    We disagree with the commenter's Request to replace the term 
``fatigue'' with ``deformation.'' The intent of the Airbus service 
information and the FAA AD is to inspect for ``fatigue cracking.'' For 
clarity, we have revised the SUMMARY and Discussion sections of this 
final rule, and paragraphs (i), (k), and (m) of this AD, by changing 
``fatigue'' to ``fatigue cracking.''

Request To Use Revised Service Information

    American Airlines (AAL) requested that we revise the proposed AD to 
reference Airbus Service Bulletin A320-52-1163, Revision 01, including 
Appendix 01, dated June 22, 2015.
    We agree with the commenter's request. No additional work is 
required by this revision of the service information. We have revised 
paragraphs (g), (i), (k), (l), and (m) of this AD to reference Airbus 
Service Bulletin A320-52-1163, Revision 01, including Appendix 01, 
dated June 22, 2015. We have added credit for the actions required by 
paragraphs (g), (i), (k), (l), and (m) of this AD, if those actions 
were performed before the effective date of this AD using Airbus 
Service Bulletin A320-52-1163, dated February 4, 2014.

Request To Revise Re-Identification of Fairing Part Number

    AAL requested that we revise paragraphs (k), (l), (m), and (n) of 
the proposed AD to remove the re-identification of the fairing part 
number specified in Airbus Service Bulletin A320-52-1165, including 
Appendix 01, dated November 3, 2014, on airplanes that are pre-Airbus 
Modification 27716 and post-modification Airbus Service Bulletin A320-
52-1100. AAL stated that a discrepancy in Airbus Service Bulletin A320-
52-1165, including Appendix 01, dated November 3, 2014, makes it 
impossible to re-identify the fairing part number.
    We agree with AAL that Airbus Service Bulletin A320-52-1165, 
including Appendix 01, dated November 3, 2014, has a discrepancy in the 
re-identification of the fairing part number. Airbus has revised the 
instructions for re-identification of the fairing part number for pre-
Airbus Modification 27716 and post-modification Airbus Service Bulletin 
A320-52-1100 configuration airplanes in Airbus Service Bulletin A320-
52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01, 
dated November 3, 2014, and including Appendix 02, dated October 23, 
2015. We have revised paragraphs (k), (l)(1), (m), and (n)(3) of this 
AD to reference Airbus Service Bulletin A320-52-1165, Revision 01, 
dated October 23, 2015, excluding Appendix 01, dated November 3, 2014, 
and including Appendix 02, dated October 23, 2015, as the appropriate 
source of service information for the applicable actions in those 
paragraphs.

[[Page 26117]]

Request To Specify Allowable Corrosion Limits

    AAL requested that we specify the allowable corrosion limits that 
would allow release of the airplane into service with corroded stud 
assemblies. AAL stated that paragraph (l)(2) of the proposed AD allows 
an operator to release an airplane into service with corrosion on the 
stud assembly, without accomplishing any corrective action at the time 
of the corrosion findings, provided that the stud assembly is not 
loose.
    We disagree with the commenter's request to specify corrosion 
limits in the AD. The corrosion level(s) and subsequent action(s) in 
general are defined in the AAL corrosion prevention and corrosion 
control maintenance program (CPCP). For this AD, operators have an 
option to either replace the affected stud assemblies (that have 
corrosion but the corroded stud is not loose) before further flight as 
specified in paragraph (l)(1) of this AD or perform repetitive 
inspections as specified in paragraph (l)(2) of this AD until 
corrective actions are done as specified in paragraph (m) of this AD. 
We have not changed this AD in this regard.

Request to Add Paragraph To Specify No Reporting Is Required

    UAL requested that we add a paragraph in the proposed AD, to remove 
the Airbus Service Bulletin A320-52-1163, dated February 4, 2014, 
requirement to report all inspection findings to Airbus.
    We agree with the commenter's request. We have added new paragraph 
(q) to this AD, which states that although Airbus Service Bulletin 
A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015, 
specifies to submit certain information to the manufacturer, and 
specifies that action as ``RC'' (Required for Compliance), this AD does 
not include that requirement. We have redesignated subsequent 
paragraphs accordingly. Although not required to do so by this AD, we 
recommend that operators submit such information based on the Airbus 
service information request. This information may be beneficial to 
Airbus for product improvements.

Request To Clarify Repetitive Inspection Interval

    AAL requested clarification of the repetitive inspection interval 
in paragraph (l)(2) of the proposed AD. AAL stated that, if Airbus 
Service Bulletin A320-52-1163, Revision 01, including Appendix 01, 
dated June 22, 2015, was referenced in this AD, this service 
information includes an option for a repetitive inspection interval of 
750 flight cycles.
    We agree to clarify the repetitive inspection interval in paragraph 
(l)(2) of this AD. The 4-month repetitive inspection interval specified 
in paragraph (l)(2) of this AD has precedence over the 750-flight-cycle 
interval specified in Airbus Service Bulletin A320-52-1163, Revision 
01, including Appendix 01, dated June 22, 2015. We have not changed 
this AD in this regard.

Request To Revise Corrective Actions

    Delta Airlines (DAL) requested that we revise paragraph (k) of the 
proposed AD to require the replacement of only the affected assembly 
and not the upper and lower fixed fairing forward attachment assemblies 
of the LH and RH MLG because of one finding on an affected assembly. 
DAL stated that paragraph (k) of the proposed AD places an undue burden 
on operators by having to replace airworthy parts because one of the 
affected parts was found with a finding of corrosion, wear, fatigue 
cracking, or loose studs.
    We agree with the commenter's request. We agree with DAL that only 
parts with indication of corrosion, wear, fatigue cracking, or loose 
studs should be replaced. We have revised paragraph (k) of this AD to 
require replacing discrepant upper and lower fixed fairing forward 
attachment stud assemblies of the LH and RH MLG.

Request To Revise Exceptions to AD Actions

    DAL requested that we revise paragraph (o) of the proposed AD to 
indicate that paragraphs (g) through (n) of the proposed AD are not 
applicable to post-Airbus Modification 155648 configuration airplanes. 
DAL stated that paragraph (o) of the proposed AD provides relief from 
the requirements of paragraphs (g) and (i) of the proposed AD, but 
related paragraphs (h), (j), (k), (l), and (n) of the proposed AD are 
not included in the relief.
    We agree with the commenter that the intent of this AD is to not 
require paragraphs (g) through (n) of this AD if conditions stated in 
paragraph (o) of this AD are met. The requirements of paragraphs (k), 
(l), and (m) of this AD are conditional and will not apply to operators 
that are not required to do paragraphs (g) and (i) of this AD. 
Paragraph (n) of this AD is an explanation of terminating actions. We 
have clarified paragraphs (h) and (j) of this AD to refer to the exempt 
airplanes.

Request To Delete Paragraph (p)(1) of the Proposed AD, and Change 
Wording in Paragraphs (p)(1) Through (p)(4) of the Proposed AD

    DAL requested that we delete paragraph (p)(1) of the proposed AD. 
DAL stated that paragraph (p)(1) of the proposed AD applies to pre-
Airbus Modification 27716 and pre-Airbus Service Bulletin A320-52-1100 
configuration airplanes, but provides a requirement for post-Airbus 
Modification 27716 or post-Airbus Service Bulletin A320-52-1100 
configuration airplanes, which is redundant with the requirements of 
paragraph (p)(2) of the proposed AD. Delta also requested that we 
replace the word ``and'' in paragraphs (p)(1) through (p)(4) of the 
proposed AD with ``or'' to clarify the requirement and be consistent 
with the wording used in paragraph (i) of the proposed AD.
    We partially agree with the commenter's requests. We agree with DAL 
to revise paragraphs (p)(1) through (p)(4) of this AD to replace 
``and'' with ``or.'' We do not agree with deleting paragraph (p)(1) of 
this AD. Paragraph (p)(1) of this AD is applicable for airplanes in 
pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-
1100 configuration, and the parts prohibition is effective after doing 
the actions provided in paragraph (n)(2) of this AD. Paragraph (p)(2) 
of this AD is applicable for airplanes in post-Airbus Modification 
27716 or post-Airbus Service Bulletin A320-52-1100 configuration, and 
the parts prohibition is effective as of the effective date of this AD. 
Therefore, paragraphs (p)(1) and (p)(2) of this AD are not redundant. 
We have not changed this AD in this regard.

Request To Delete Paragraph (p)(3) of the Proposed AD

    DAL requested that we delete paragraph (p)(3) of the proposed AD. 
DAL stated that paragraph (p)(3) of the proposed AD applies to pre-
Airbus Modification 155648 and pre-Airbus Service Bulletin A320-52-1165 
configuration airplanes, but provides a requirement for post-Airbus 
Modification 155648 or post-Airbus Service Bulletin A320-52-1165, which 
is redundant with the requirements of paragraph (p)(4) of the proposed 
AD.
    We do not agree with the commenter's request. Paragraph (p)(3) of 
this AD is applicable for airplanes which have not been modified to 
post-Airbus Modification 155648 or post-Airbus Service Bulletin A320-
52-1165 configuration. Paragraph (p)(4) of this AD is applicable for 
airplanes that are in post-Airbus Modification 155648 or

[[Page 26118]]

post-Airbus Service Bulletin A320-52-1165 configuration. We have not 
changed this AD in this regard.

Conclusion

    We reviewed the relevant data, considered the comments received, 
and determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
     Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM.
    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed the following service information:
     Airbus Service Bulletin A320-52-1100, Revision 01, dated 
March 12, 1999. This service information describes procedures for 
modification of the airplane to post-Airbus Modification 27716 
configuration (by replacing the location stud, rod end, and location 
plate at the forward upper and lower leg fixed-fairing positions of the 
MLG door assemblies). The modification includes a resonance frequency 
inspection for debonding of the composite insert and delamination of 
the honeycomb area around the insert, and applicable corrective 
actions. Corrective actions include repairing the insert. The actions 
in this service information are an optional terminating modification.
     Airbus Service Bulletin A320-52-1163, Revision 01, 
including Appendix 01, dated June 22, 2015. This service information 
describes procedures for inspection of the fixed fairing forward 
attachments of the MLG door assemblies, and replacement of the fixed 
fairing upper and lower attachment studs of the LH and RH MLG door 
assemblies.
     Airbus Service Bulletin A320-52-1165, Revision 01, dated 
October 23, 2015, excluding Appendix 01, dated November 3, 2014, and 
including Appendix 02, dated October 23, 2015. This service information 
describes procedures for replacing the fairing attachment stud 
assemblies of the MLG door assembly with new assemblies. The actions in 
this service information are an optional terminating modification.
    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.

Explanation of ``RC'' (Required for Compliance) (RC) Procedures and 
Tests in Service Information

    The FAA worked in conjunction with industry, under the 
Airworthiness Directive Implementation Aviation Rulemaking Committee 
(ARC), to enhance the AD system. One enhancement was a new process for 
annotating which procedures and tests in the service information are 
required for compliance with an AD. Differentiating these procedures 
and tests from other tasks in the service information is expected to 
improve an owner's/operator's understanding of crucial AD requirements 
and helps to provide consistent judgment in AD compliance. The 
procedures and tests identified as RC in any service information have a 
direct effect on detecting, preventing, resolving, or eliminating an 
identified unsafe condition.
    As specified in a NOTE under the Accomplishment Instructions of the 
specified service information, procedures and tests that are identified 
as RC in any service information must be done to comply with the AD. 
However, procedures and 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 alternative method of compliance (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 will require approval of an AMOC.

Costs of Compliance

    We estimate that this AD affects 851 airplanes of U.S. registry.
    We also estimate that it will take about 18 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Required parts will cost about $4,110 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $4,799,640, or $5,640 per product.
    We estimate that the optional terminating modification would take 
about 18 work-hours and require parts costing $4,110, for a cost of 
$5,640 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 18 work-hours and require parts costing $4,110, for a cost 
of $5,640 per product. We have no way of determining the number of 
aircraft that might need these actions.
    According to the manufacturer, some of the costs of this AD might 
be covered under warranty, thereby reducing the cost impact on affected 
individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

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.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2015-2458; or in

[[Page 26119]]

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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority:  49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by adding the following new airworthiness 
directive (AD):

2016-07-23 Airbus: Amendment 39-18468. Docket No. FAA-2015-2458; 
Directorate Identifier 2014-NM-122-AD.

(a) Effective Date

    This AD becomes effective June 6, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A318-111, -112, -121, and -122 airplanes.
    (2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, 
and -133 airplanes.
    (3) Airbus Model A320-211, -212, -214, -231, -232, and -233 
airplanes.
    (4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, 
and -232 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 52, Doors.

(e) Reason

    This AD was prompted by reports of in-flight loss of fixed and 
hinged main landing gear (MLG) fairings, and reports of post-
modification MLG fixed fairing assemblies that have wear and 
corrosion. We are issuing this AD to prevent in-flight detachment of 
an MLG fixed fairing and consequent damage to the airplane.

(f) Compliance

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

(g) Repetitive Replacements

    For airplanes in pre-Airbus Modification 27716 and pre-Airbus 
Service Bulletin A320-52-1100 configuration, with any of the 
components installed that are identified in paragraphs (g)(1) 
through (g)(5) of this AD: At the applicable compliance time 
specified in paragraph (h) of this AD, replace fixed fairing upper 
and lower attachment studs of both left-hand (LH) and right-hand 
(RH) MLG, in accordance with the Accomplishment Instructions of 
Airbus Service Bulletin A320-52-1163, Revision 01, including 
Appendix 01, dated June 22, 2015. Repeat the replacements thereafter 
at intervals not to exceed 6,500 flight cycles.
    (1) Plate--support having part number (P/N) D5284024820000.
    (2) Plate--support P/N D5284024820200.
    (3) Stud--adjustment having P/N D5284024420000.
    (4) Rod end assembly (lower) having P/N D5284000500000.
    (5) Rod end assembly (upper) having P/N D5284000600000.

(h) Compliance Times for the Requirements of Paragraph (g) of This AD

    For airplanes identified in paragraph (g) of this AD, except as 
provided by paragraph (o) of this AD: Do the initial replacement 
required by paragraph (g) of this AD at the latest of the times 
specified in paragraphs (h)(1) through (h)(4) of this AD.
    (1) Before the accumulation of 6,500 total flight cycles since 
the airplane's first flight.
    (2) Within 6,500 flight cycles since the last installation of a 
pre-Airbus Modification 27716 stud on the airplane.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(i) Repetitive Inspections

    For airplanes in post-Airbus Modification 27716 or post-Airbus 
Service Bulletin A320-52-1100 configuration, with any of the 
components installed that are identified in paragraphs (i)(1), 
(i)(2), and (i)(3) of this AD: At the applicable compliance time 
specified in paragraph (j) of this AD, do a detailed inspection of 
the LH and RH MLG forward stud assemblies of the fixed fairing door 
upper and lower forward attachments of both LH and RH MLG for 
indications of corrosion, wear, fatigue cracking, and loose studs, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated 
June 22, 2015. Repeat the inspection thereafter at intervals not to 
exceed 12 months. Replacement of both LH and RH MLG forward stud 
assemblies on an airplane, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1163, Revision 01, 
including Appendix 01, dated June 22, 2015, extends the interval for 
the next detailed inspection to 72 months; and the inspection must 
be repeated thereafter at intervals not to exceed 12 months.
    (1) Stud--adjustment having P/N D5285600720000.
    (2) Rod end assembly (lower) having P/N D5285600400000.
    (3) Rod end assembly (upper) having P/N D5285600500000.

(j) Compliance Times for the Requirements of Paragraph (i) of This AD

    For airplanes identified in paragraph (i) of this AD, except as 
provided by paragraph (o) of this AD: Do the initial inspection 
required by paragraph (i) of this AD at the latest of the times 
specified in paragraphs (j)(1) through (j)(4) of this AD.
    (1) Before the accumulation of 72 months since the airplane's 
first flight.
    (2) Within 72 months since the last installation of a post-
Airbus Modification 27716 assembly or since accomplishment of the 
actions specified in Airbus Service Bulletin A320-52-1100.
    (3) Within 1,500 flight cycles after the effective date of this 
AD.
    (4) Within 8 months after the effective date of this AD.

(k) Corrective Action

    If any discrepancy (including any indication of corrosion, wear, 
fatigue cracking, or loose studs) of any MLG forward stud assembly 
is found during any inspection required by paragraph (i) of this AD, 
except as specified in paragraph (l) of this AD: Before further 
flight, replace the discrepant upper and lower fixed fairing forward 
stud assemblies of the LH and RH MLG, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163, 
Revision 01, including Appendix 01, dated June 22, 2015; or Airbus 
Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015, 
excluding Appendix 01, dated November 3, 2014, and including 
Appendix 02, dated October 23, 2015.

(l) Corrective Action or Repetitive Inspections for Certain Corrosion 
Findings

    If any corrosion is found during any inspection required by 
paragraph (i) of this AD on any MLG fixed fairing forward stud 
assembly (upper, lower, LH or RH), but the corroded stud is not 
loose: Do the action specified in paragraph (l)(1) or (l)(2) of this 
AD.
    (1) Before further flight, replace the affected assembly, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated 
June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, 
dated October 23, 2015, excluding Appendix 01, dated November 3, 
2014, and including Appendix 02, dated October 23, 2015.
    (2) Within 4 months after finding corrosion, and thereafter at 
intervals not to exceed 4 months, do a detailed inspection for 
indications of corrosion, wear, fatigue cracking, and loose studs of 
the forward stud assembly of the affected (LH or RH) MLG, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated 
June 22, 2015.

[[Page 26120]]

(m) Corrective Action for Inspections Specified in Paragraph (l)(2) of 
This AD

    If any indication of wear, fatigue cracking, or loose studs of 
any forward stud assembly is found during any inspection required by 
paragraph (l)(2) of this AD: Before further flight, replace the 
affected (LH or RH) MLG fixed fairing forward stud assembly, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated 
June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01, 
dated October 23, 2015, excluding Appendix 01, dated November 3, 
2014, and including Appendix 02, dated October 23, 2015.

(n) Terminating Action

    (1) Replacement of parts on an airplane, as required by 
paragraph (g), (k), (l)(1), or (m) of this AD, does not constitute 
terminating action for the repetitive inspections required by 
paragraph (i) of this AD, except as specified in paragraph (n)(3) of 
this AD.
    (2) The repetitive replacements required by paragraph (g) of 
this AD may be terminated by modification of the airplane to post-
Airbus Modification 27716 configuration, including a resonance 
frequency inspection for debonding of the composite insert and 
delamination of the honeycomb area around the insert, and all 
applicable corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-52-1100, Revision 01, 
dated March 12, 1999, provided all applicable corrective actions are 
done before further flight. Thereafter, refer to paragraph (i) of 
this AD to determine the compliance time for the next detailed 
inspection required by this AD.
    (3) Modification of an airplane, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165, 
Revision 01, dated October 23, 2015, excluding Appendix 01, dated 
November 3, 2014, and including Appendix 02, dated October 23, 2015, 
constitutes terminating action for actions required by paragraphs 
(g) through (m) of this AD for the airplane on which the 
modification is done.

(o) Exceptions to Certain AD Actions

    An airplane on which Airbus Modification 155648 has been 
embodied in production is not affected by the requirements of 
paragraphs (g) and (i) of this AD, provided that no affected 
component, identified by part number as listed paragraphs (g)(1) 
through (g)(5) and (i)(1) through (i)(3) of this AD, has been 
installed on that airplane since first flight of the airplane.

(p) Parts Installation Prohibition

    (1) For airplanes in pre-Airbus Modification 27716 or pre-Airbus 
Service Bulletin A320-52-1100 configuration: No person may install a 
component identified in paragraphs (g)(1) through (g)(5) of this AD 
on any airplane after doing the actions provided in paragraph (n)(2) 
of this AD.
    (2) For airplanes in post-Airbus Modification 27716 or post 
Airbus Service Bulletin A320-52-1100 configuration: As of the 
effective date of this AD, no person may install a component 
identified in paragraphs (g)(1) through (g)(5) of this AD on any 
airplane.
    (3) For airplanes in pre-Airbus Modification 155648 or pre-
Airbus Service Bulletin A320-52-1165 configuration: No person may 
install a component identified in paragraphs (g)(1) through (g)(5) 
and (i)(1) through (i)(3) of this AD on any airplane after doing the 
actions provided in paragraph (n)(3) of this AD.
    (4) For airplanes in post-Airbus Modification 155648 or post-
Airbus Service Bulletin A320-52-1165 configuration: As of the 
effective date of this AD, no person may install a component 
identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of 
this AD on any airplane.

(q) No Reporting Requirement

    Although Airbus Service Bulletin A320-52-1163, Revision 01, 
including Appendix 01, dated June 22, 2015, specifies to submit 
certain information to the manufacturer, and specifies that action 
as ``RC'' (Required for Compliance), this AD does not include that 
requirement.

(r) Credit for Previous Actions

    (1) This paragraph provides credit for optional actions provided 
by paragraph (n)(2) of this AD, if those actions were performed 
before the effective date of this AD using Airbus Service Bulletin 
A320-52-1100, dated December 7, 1998, which is not incorporated by 
reference in this AD.
    (2) This paragraph provides credit for the actions required by 
paragraphs (g), (i), (k), (l), and (m) of this AD, if those actions 
were performed before the effective date of this AD using Airbus 
Service Bulletin A320-52-1163, dated February 4, 2014, which is not 
incorporated by reference in this AD.

(s) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, Transport Airplane Directorate, 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 ATTN: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. 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. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, 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 specified in 
paragraph (q) 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.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0001R1, dated January 15, 
2015, 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-2015-2458.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (u)(3) and (u)(4) of this AD.

(u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A320-52-1100, Revision 01, dated 
March 12, 1999.
    (ii) Airbus Service Bulletin A320-52-1163, Revision 01, 
including Appendix 01, dated June 22, 2015.
    (iii) Airbus Service Bulletin A320-52-1165, Revision 01, dated 
October 23, 2015, excluding Appendix 01, dated November 3, 2014, and 
including Appendix 02, dated October 23, 2015.
    (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.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 26121]]

    Issued in Renton, Washington, on April 13, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-09119 Filed 4-29-16; 8:45 am]
 BILLING CODE 4910-13-P
```