[Federal Register Volume 81, Number 72 (Thursday, April 14, 2016)]
[Proposed Rules]
[Pages 22033-22037]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-08367]


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

  Federal Register / Vol. 81, No. 72 / Thursday, April 14, 2016 / 
Proposed Rules  

[[Page 22033]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5589; Directorate Identifier 2014-NM-252-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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

SUMMARY: We propose to supersede Airworthiness Directive (AD) 2012-20-
07, for certain Airbus Model A318, A319, A320, and A321 series 
airplanes. AD 2012-20-07 currently requires revising the airworthiness 
limitations section (ALS) of the instructions for continued 
airworthiness (ICA) to incorporate new limitations for fuel tank 
systems, and revising the maintenance program to incorporate revised 
fuel maintenance and inspection tasks. Since we issued AD 2012-20-07, 
Airbus has issued more restrictive maintenance requirements and/or 
airworthiness limitations. This proposed AD would require revising the 
maintenance or inspection program to incorporate revised fuel 
airworthiness limitations. We are proposing this AD to prevent the 
potential of ignition sources inside fuel tanks, which, in combination 
with flammable fuel vapors, could result in a fuel tank explosion and 
consequent loss of the airplane.

DATES: We must receive comments on this proposed AD by May 31, 2016.

ADDRESSES: You may send comments 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: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this NPRM, contact Airbus, 
Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email [email protected]; Internet http://www.airbus.com. You may view this referenced service information at the 
FAA, Transport Airplane Directorate, 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-2016-
5589; 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 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: 

Comments Invited

    We invite you to send any written relevant data, views, or 
arguments about this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-5589; 
Directorate Identifier 2014-NM-252-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

    On October 2, 2012, we issued AD 2012-20-07, Amendment 39-17213 (77 
FR 63716, October 17, 2012) (``AD 2012-20-07''). AD 2012-20-07 requires 
actions intended to address an unsafe condition on all Model A319, 
A320, and A321 series airplanes.
    Since we issued AD 2012-20-07, Airbus has issued A318/A319/A320/
A321 Airworthiness Limitations Section (ALS) Part 5, Fuel Airworthiness 
Limitations, Revision 01, dated July 9, 2014, which contains more 
restrictive maintenance requirements and/or airworthiness limitations. 
The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2014-0260, dated December 5, 2014 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition. The MCAI states:

    Prompted by an accident . . ., the Federal Aviation 
Administration (FAA) published Special Federal Aviation Regulation 
(SFAR) 88 [http://rgl.faa.gov/Regulatory_and_Guidance_Library/rgFAR.nsf/0/EEFB3F94451DC06286256C93004F5E07?OpenDocument&Highlight=sfar 88], 
and the Joint Aviation Authorities (JAA) published interim Policy 
INT/POL/25/12. In response to these regulations, Airbus conducted a 
design review to develop Fuel Airworthiness Limitations (FAL) for 
Airbus A320 family aeroplanes.
    The FAL were specified in Airbus A318/A319/A320/A321 FAL 
document ref. 95A.1931/05 at issue 04 for A318/A319/A320/A321 
aeroplanes. This document was approved by the European Aviation 
Safety Agency (EASA) and is now referenced in Airbus A318/A319/A320/
A321 ALS Part 5 to comply with EASA policy statement (EASA D2005/
CPRO).
    Failure to comply with items as identified in Airbus A318/A319/
A320/A321 ALS Part 5 could result in a fuel tank explosion and 
consequent loss of the aeroplane.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0155R1 (http://ad.easa.europa.eu/

[[Page 22034]]

blob/easa_ad_2011_0155_R1_superseded.pdf/AD_2011-0155R1_1), which is 
superseded [and which corresponds to FAA AD 2012-20-07, Amendment 
39-17213 (77 FR 63716, October 17, 2012)], and requires 
implementation of the new or more restrictive maintenance 
requirements and/or airworthiness limitations as specified in Airbus 
A318/A319/A320/A321 ALS Part 5 at Rev.01.
* * * * *
    The required action is revising the maintenance or inspection 
program to incorporate revised fuel airworthiness limitations.
    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-2016-
5589.

Related Service Information Under 1 CFR Part 51

    Airbus has issued A318/A319/A320/A321 ALS Part 5, Fuel 
Airworthiness Limitations, Revision 01, dated July 9, 2014. The service 
information describes fuel system airworthiness limitations. 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 [hairsp]This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.
    This proposed AD requires revisions to certain operator maintenance 
documents to include new actions (e.g., inspections) and/or Critical 
Design Configuration Control Limitations (CDCCLs). Compliance with 
these actions and/or CDCCLs is required by 14 CFR 91.403(c). For 
airplanes that have been previously modified, altered, or repaired in 
the areas addressed by this proposed AD, the operator may not be able 
to accomplish the actions described in the revisions. In this 
situation, to comply with 14 CFR 91.403(c), the operator must request 
approval for an alternative method of compliance according to paragraph 
(n)(1) of this proposed AD. The request should include a description of 
changes to the required inspections that will ensure the continued 
operational safety of the airplane.
    Notwithstanding any other maintenance or operational requirements, 
components that have been identified as airworthy or installed on the 
affected airplanes before accomplishing the revision of the airplane 
maintenance or inspection program or before accomplishing the revision 
of the Airworthiness Limitation Section (ALS) of the Instructions for 
Continued Airworthiness specified in this proposed AD, do not need to 
be reworked in accordance with the CDCCLs. However, once the airplane 
maintenance or inspection program or ALS has been revised as required 
by this proposed AD, future maintenance actions on these components 
must be done in accordance with the CDCCLs.

Differences Between This Proposed AD and the MCAI or Service 
Information

    The MCAI specifies that if there are findings from the ALS 
inspection tasks, corrective actions must be accomplished in accordance 
with Airbus maintenance documentation. However, this proposed AD does 
not include that requirement. Operators of U.S.-registered airplanes 
are required by general airworthiness and operational regulations to 
perform maintenance using methods that are acceptable to the FAA. We 
consider those methods to be adequate to address any corrective actions 
necessitated by the findings of ALS inspections required by this 
proposed AD.

Explanation of Proposed Compliance Time

    In most ADs, we adopt a compliance time allowing a specified amount 
of time after the AD's effective date or as specified by the MCAI, 
whichever is later. In this case, however, the MCAI compliance time has 
already expired. We have determined that an appropriate initial 
compliance time is 60 days for revising the maintenance or inspection 
program to incorporate the fuel airworthiness limitations (e.g., life 
limits, tasks, and CDCCLs, and associated thresholds and intervals) 
described in Airbus A318/A319/A320/A321 ALS Part 5, Fuel Airworthiness 
Limitations, Revision 01, dated July 9, 2014. We find 60 days an 
appropriate compliance time to revise the maintenance or inspection 
program. The initial compliance times for the tasks are at the times 
specified in Airbus A318/A319/A320/A321 ALS Part 5, Fuel Airworthiness 
Limitations, Revision 01, dated July 9, 2014, or within 60 days, 
whichever is later. In developing the compliance time for this action, 
we considered the degree of urgency associated with addressing the 
unsafe condition. This difference has been coordinated with the EASA.

Airworthiness Limitations Based on Type Design

    The FAA recently became aware of an issue related to the 
applicability of ADs that require incorporation of an ALS revision into 
an operator's maintenance or inspection program.
    Typically, when these types of ADs are issued by civil aviation 
authorities of other countries, they apply to all airplanes covered 
under an identified type certificate (TC). The corresponding FAA AD 
typically retains applicability to all of those airplanes.
    In addition, U.S. operators must operate their airplanes in an 
airworthy condition, in accordance with 14 CFR 91.7(a). Included in 
this obligation is the requirement to perform any maintenance or 
inspections specified in the ALS, and in accordance with the ALS as 
specified in 14 CFR 43.16 and 91.403(c), unless an alternative has been 
approved by the FAA.
    When a type certificate is issued for a type design, the specific 
ALS, including revisions, is a part of that type design, as specified 
in 14 CFR 21.31(c).
    The sum effect of these operational and maintenance requirements is 
an obligation to comply with the ALS defined in the type design 
referenced in the manufacturer's conformity statement. This obligation 
may introduce a conflict with an AD that requires a specific ALS 
revision if new airplanes are delivered with a later revision as part 
of their type design.
    To address this conflict, the FAA has approved alternative methods 
of compliance (AMOCs) that allow operators to incorporate the most 
recent ALS revision into their maintenance/inspection programs, in lieu 
of the ALS revision required by the AD. This eliminates the conflict 
and enables the operator to comply with both the AD and the type 
design.
    However, compliance with AMOCs is normally optional, and we 
recently became aware that some operators choose to retain the AD-
mandated ALS revision in their fleet-wide maintenance/inspection 
programs, including those for new airplanes delivered with later ALS 
revisions, to help standardize the maintenance of the fleet. To ensure 
that operators comply with the applicable ALS revision for newly 
delivered airplanes containing a later revision than that specified in 
an AD, we plan to limit the applicability of ADs that mandate ALS 
revisions to those airplanes that are subject to an earlier revision of 
the ALS, either as part

[[Page 22035]]

of the type design or as mandated by an earlier AD.
    This proposed AD therefore applies to the airplanes identified in 
paragraph (c) of this proposed AD with an original certificate of 
airworthiness or original export certificate of airworthiness that was 
issued on or before the date of approval of the ALS revision identified 
in this proposed AD. Operators of airplanes with an original 
certificate of airworthiness or original export certificate of 
airworthiness issued after that date must comply with the airworthiness 
limitations specified as part of the approved type design and 
referenced on the type certificate data sheet.

Record of Ex Parte Communication

    In preparation of AD actions, it is the practice of the FAA to 
obtain technical information and information on the operational and 
economic impact from design approval holders and aircraft operators. We 
discussed certain issues related to this NPRM in a recent meeting with 
Airlines for America (A4A). Shortly after this NPRM is published, we 
will post a summary of this meeting in the rulemaking docket. For 
information on locating the docket, see ``Examining the AD Docket.''

Costs of Compliance

    We estimate that this proposed AD affects 953 airplanes of U.S. 
registry.
    The actions required by AD 2012-20-07, and retained in this 
proposed AD take about 4 work-hours per product, at an average labor 
rate of $85 per work-hour. Based on these figures, the estimated cost 
of the actions that are required by AD 2012-20-07 is $340 per product.
    We also estimate that it would take about 1 work-hour per product 
to comply with the basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Based on these figures, we estimate 
the cost of this proposed AD on U.S. operators to be $81,005, or $85 
per product.

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 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) 
2012-20-07, Amendment 39-17213 (77 FR 63716, October 17, 2012), and 
adding the following new AD:

Airbus: Docket No. FAA-2016-5589; Directorate Identifier 2014-NM-
252-AD.

(a) Comments Due Date

    We must receive comments by May 31, 2016.

(b) Affected ADs

    This AD replaces AD 2012-20-07, Amendment 39-17213 (77 FR 63716, 
October 17, 2012) (``AD 2012-20-07'').

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) through (c)(4) of this AD, certificated in any category, with 
an original certificate of airworthiness or original export 
certificate of airworthiness issued on or before July 19, 2014.
    (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.
    (4) Model A321-111, -112, -131, -211, -212, -213, -231, and -232 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 05, Periodic 
inspections.

(e) Reason

    This AD was prompted by Airbus issuing more restrictive 
maintenance requirements and/or airworthiness limitations. We are 
issuing this AD to prevent the potential of ignition sources inside 
fuel tanks, which, in combination with flammable fuel vapors, could 
result in a fuel tank explosion and consequent loss of the airplane.

(f) Compliance

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

(g) Retained Revision of the Airworthiness Limitations Section (ALS) To 
Incorporate Fuel Maintenance and Inspection Tasks, With No Changes

    This paragraph restates the requirements of paragraph (g) of AD 
2012-20-07, with no changes. For Model A318-111 and -112 airplanes, 
and Model A319, A320, and A321 airplanes: Within 3 months after 
August 28, 2007 (the effective date of AD 2007-15-06 (72 FR 40222, 
July 24, 2007) (``AD 2007-15-06'')), revise the ALS of the 
Instructions for Continued Airworthiness to incorporate Airbus A318/
A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated 
February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel 
Airworthiness Limitations, Document 95A.1931/05, Issue 1, dated 
December 19, 2005 (approved by the European Aviation Safety Agency 
(EASA) on March 14, 2006), Section 1, ``Maintenance/Inspection 
Tasks;'' or Airbus A318/A319/A320/A321 Fuel Airworthiness 
Limitations, Document 95A.1931/05, Issue 2, dated July 8, 2008 
(approved by the EASA on December 19, 2008), Section 1, 
``Maintenance/Inspection Tasks.'' For all tasks identified in 
Section 1 ``Maintenance/Inspection Tasks,'' of Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, 
Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008; 
the initial compliance times start from August 28, 2007 (the 
effective date of AD 2007-15-06), and the repetitive inspections 
must be accomplished thereafter at the intervals specified in 
Section 1, ``Maintenance/Inspection Tasks,'' of Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, 
Issue 1, dated December 19, 2005; or Issue 2, dated July 8, 2008.


[[Page 22036]]


    Note 1 to paragraph (g) of this AD:  Airbus Operator Information 
Telex (OIT) SE 999.0076/06, dated June 20, 2006, provides guidance 
on identifying the applicable sections of the Airbus A318/A319/A320/
A321 Airplane Maintenance Manual for accomplishing the tasks 
specified in Section 1 ``Maintenance/Inspection Tasks,'' of Airbus 
A318/A319/A320/A321 Fuel Airworthiness Limitations, Document 
95A.1931/05, Issue 1, dated December 19, 2005; or Issue 2, dated 
July 8, 2008.

(h) Retained Revision of the ALS to Incorporate Critical Design 
Configuration Control Limitations (CDCCLs), With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-20-07, with no changes. For Airbus Model A318-111 and -112 
airplanes, and Model A319, A320, and A321 airplanes: Within 12 
months after August 28, 2007 (the effective date of AD 2007-15-06), 
revise the ALS of the Instructions for Continued Airworthiness to 
incorporate Airbus A318/A319/A320/A321 ALS Part 5-Fuel Airworthiness 
Limitations, dated February 28, 2006, as defined in Airbus A318/
A319/A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, 
Issue 1, dated December 19, 2005 (approved by the European Aviation 
Safety Agency (EASA) on March 14, 2006), Section 2, ``Critical 
Design Configuration Control Limitations;'' or Airbus A318/A319/
A320/A321 Fuel Airworthiness Limitations, Document 95A.1931/05, 
Issue 2, dated July 8, 2008 (approved by EASA on December 19, 2008), 
Section 2, ``Critical Design Configuration Control Limitations.''

(i) Retained Requirement: No Alternative Inspections, Inspection 
Intervals, or CDCCLs, With No Changes

    This paragraph restates the requirements of paragraph (i)(1) of 
AD 2012-20-07, with no changes.
    Except as required by paragraph (l) of this AD and except as 
provided by paragraph (n)(1) of this AD: After accomplishing the 
actions specified in paragraphs (g) and (h) of this AD, no 
alternative inspections, inspection intervals, or CDCCLs may be 
used.

(j) Retained Revision of the Maintenance Program, With Specific 
Delegation Approval Language in Paragraph (j)(4) of This AD

    This paragraph restates the requirements of paragraph (j) of AD 
2012-20-07, with specific delegation approval language in paragraph 
(j)(4) of this AD. Within 6 months after November 21, 2012 (the 
effective date of AD 2012-20-07): Revise the maintenance program to 
incorporate the new or revised tasks, life limits, and CDCCLs 
specified in Airbus A318/A319/A320/A321 Fuel Airworthiness 
Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, 
except as required in paragraph (j)(4) of this AD. The initial 
compliance times and intervals are stated in this ALS document, 
except as required in paragraphs (j)(1) through (j)(4) of this AD, 
or within 6 months after November 21, 2012, whichever occurs later. 
For certain tasks, the compliance times depend on the pre-
modification and post-modification status of the airplane. 
Incorporating the requirements of this paragraph terminates the 
corresponding requirements of paragraphs (g) and (h) of this AD 
only.
    (1) For airplanes for which the first flight occurred before 
August 28, 2007 (the effective date of AD 2007-15-06), the first 
accomplishment of Tasks 281800-01-1, Functional Check of Tank Vapour 
Seal and Vent Drain System; and 281800-02-1, Detailed Inspection of 
Vapour Seal; must be performed no later than 11 months after 
November 21, 2012 (the effective date of AD 2012-20-07).
    (2) The first accomplishment of Tasks 470000-01-1, Operational 
Check of Dual Flapper Shutoff Valves (DFSOV), Dual Flapper Check 
Valves and Nitrogen Enriched Air (NEA) Line for Leaks; 470000-02-1, 
Operational Check of Both Dual Flapper Check Valves for Leaks; 
470000-03-1, Operational Check of Dual Flapper Check Valves for 
Reverse Flow and NEA Line for Leaks; 470000-04-1, Operational Check 
of Dual Flapper Check Valves for Reverse Flow; and 470000-05-1, 
Remove Air Separation Module (ASM) and Return to Vendor for Workshop 
Check; must be calculated, in accordance with paragraph (j)(2)(i) or 
(j)(2)(ii) of this AD.
    (i) From the airplane first flight for airplanes on which Airbus 
modification 38062 or 38195 has been embodied in production.
    (ii) From the in-service installation of the fuel tank inerting 
system specified in Airbus Service Bulletin A320-47-1001, Airbus 
Service Bulletin A320-47-1002, Airbus Service Bulletin A320-47-1003, 
Airbus Service Bulletin A320-47-1004, Airbus Service Bulletin A320-
47-1006, or Airbus Service Bulletin A320-47-1007.
    (3) Although Airbus A318/A319/A320/A321 Fuel Airworthiness 
Limitations, Document 95A.1931/05, Issue 4, dated August 26, 2010, 
does not refer to Airbus Service Bulletin A320-47-1006 and Airbus 
Service Bulletin A320-47-1007, the tasks apply as specified in 
paragraphs (j)(3)(i) through (j)(3)(iv) of this AD.
    (i) Tasks 470000-01-1, Operational Check of DFSOV, Dual Flapper 
Check Valves and NEA Line for Leaks; and 470000-02-1, Operational 
Check of Both Dual Flapper Check Valves for leaks; apply to 
airplanes that have previously accomplished the actions specified in 
Airbus Service Bulletin A320-47-1007.
    (ii) Task 470000-03-1, Operational Check of Dual Flapper Check 
Valves for Reverse Flow and NEA Line for Leaks, applies to airplanes 
that have previously accomplished the actions specified in Airbus 
Service Bulletin A320-47-1006, and that have not accomplished the 
actions specified in Airbus Service Bulletin A320-47-1007.
    (iii) Task 470000-04-1, Operational Check of Dual Flapper Check 
Valves for Reverse Flow, applies to airplanes in post-modification 
38195 configuration and that have not accomplished the actions 
specified in Airbus Service Bulletin A320-47-1007.
    (iv) Task 470000-05-1, Remove ASM and return to Vendor for 
Workshop Check, applies to airplanes that have previously 
accomplished the actions specified in Airbus Service Bulletin A320-
47-1007, and are in pre-modification 151529 configuration.
    (4) Replace each ASM identified in table 1 to paragraph (j)(4) 
of this AD in accordance with a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA (or its delegated agent); or the European 
Aviation Safety Agency (EASA); or Airbus's EASA Design Organization 
Approval (DOA). The compliance time for the replacement is before 
the accumulation of 27,000 total flight hours (component time)--
i.e., the life limitation.

    Note 2 to paragraph (j)(4) of this AD:  Airbus A318/A319/A320/
A321 Aircraft Maintenance Manual Task 47-10-43-920-001-A, Air 
Separation Module Replacement, is an additional source of guidance 
for accomplishment of the removal and replacement of the ASM.


         Table 1 to Paragraph (j)(4) of This AD--ASM Replacement
------------------------------------------------------------------------
                                                              ASM Part
             Affected Airplane configuration--                  No.--
------------------------------------------------------------------------
Post-modification 38062...................................   2060017-101
Post-Airbus Service Bulletin A320-47-1002.................   2060017-101
Post-Airbus Service Bulletin A320-47-1004.................   2060017-101
Post-Airbus Service Bulletin A320-47-1007.................   2060017-101
Post-modification 152033..................................   2060017-102
Post-Airbus Service Bulletin A320-47-1011.................   2060017-102
------------------------------------------------------------------------

(k) Retained Requirement: No Alternative Actions, Intervals, and/or 
CDCCLs, With No Changes

    This paragraph restates the requirements of paragraph (k) of AD 
2012-20-07, with no changes. Except as required by paragraph (l) of 
this AD, after accomplishing the revisions required by paragraph (j) 
of this AD, no alternative actions (e.g., inspections), intervals, 
and/or CDCCLs may be used other than those specified in Airbus A318/
A319/A320/A321 ALS Part 5-Fuel Airworthiness Limitations, dated 
February 28, 2006, as defined in Airbus A318/A319/A320/A321 Fuel 
Airworthiness Limitations, Document 95A.1931/05, Issue 4, dated 
August 26, 2010, unless the actions, intervals, and/or CDCCLs are 
approved as an alternative method of compliance (AMOC) in accordance 
with the procedures specified in paragraph (n)(1) of this AD.

(l) New Requirement of This AD: Revise the Maintenance or Inspection 
Program

    Within 60 days after the effective date of this AD, revise the 
maintenance or inspection program, as applicable, by incorporating 
the fuel airworthiness limitations (e.g., life limits, tasks, and 
CDCCLs, and associated thresholds and intervals) described in Airbus 
A318/A319/A320/A321 ALS Part 5, Fuel Airworthiness Limitations, 
Revision 01, dated July 9, 2014. The initial compliance times for 
the tasks are at the times specified in Airbus A318/A319/A320/A321 
ALS Part

[[Page 22037]]

5, Fuel Airworthiness Limitations, Revision 01, dated July 9, 2014, 
or within 60 days after the effective date of this AD, whichever 
occurs later. Incorporating the requirements of this paragraph 
terminates the requirements of paragraphs (g) through (k) of this 
AD.

(m) New Requirement of This AD: No Alternative Actions, Intervals, or 
CDCCLs

    After the maintenance or inspection program has been revised as 
required by paragraph (l) of this AD, no alternative actions (e.g., 
inspections), intervals, or CDCCLs may be used unless the actions, 
intervals, or CDCCLs are approved as an AMOC in accordance with the 
procedures specified in paragraph (n)(1) of this AD.

(n) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: [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. The AMOC approval letter must specifically 
reference this AD.
    (ii) AMOCs approved previously in accordance with for AD 2012-
20-07, are approved as AMOCs for the corresponding provisions 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 Branch, ANM-116, Transport 
Airplane Directorate, FAA; or EASA; or Airbus's EASA Design 
Organization Approval (DOA). If approved by the DOA, the approval 
must include the DOA-authorized signature.

(o) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2014-0260, dated December 5, 
2014, 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-2016-5589.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA, 
Transport Airplane Directorate, 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 March 31, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08367 Filed 4-13-16; 8:45 am]
 BILLING CODE 4910-13-P