[Federal Register Volume 81, Number 161 (Friday, August 19, 2016)]
[Rules and Regulations]
[Pages 55358-55362]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-19486]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-4226; Directorate Identifier 2015-NM-095-AD; 
Amendment 39-18616; AD 2016-17-03]
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 superseding Airworthiness Directive (AD) 2003-25-07 for 
certain Airbus Model A319 and A320 series airplanes, and AD 2005-13-39 
for certain Airbus Model A321 series airplanes. AD 2003-25-07 required 
a revision to the airplane flight manual (AFM) and replacement of both 
elevator aileron computers (ELACs) having L80 standards with new ELACs 
having L81 standards. AD 2005-13-39 required a revision to the AFM, 
replacement of existing ELACs with ELACs having L83 or L91 standards, 
as applicable; and a concurrent action. Since we issued AD 2003-25-07 
and AD 2005-13-39, we have determined that new ELAC standards must be 
incorporated. The ELAC standards have been upgraded to version L97+, 
which implements enhanced angle-of-attack (AOA) monitoring to better 
detect AOA blockage, including multiple AOA blockages. This AD requires 
replacing existing ELACs with new ELACs having L97+ standards or 
revising the software in an existing ELAC to the L97+ standards, as 
applicable, which terminates the requirements of AD 2003-25-07 and AD 
2005-13-39. This AD also expands the applicability to include all 
Airbus Model A318, A319, A320, and A321 series airplanes. We are 
issuing this AD to prevent inadvertent activation of the AOA 
protections. Inadvertent activation of the AOA protections could result 
in a continuous nose-down pitch rate that could result in reduced 
controllability of the airplane.

DATES: This AD is effective September 23, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of September 23, 
2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 9, 
2005 (70 FR 38580, July 5, 2005).
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of 
January 22, 2004 (68 FR 70431, December 18, 2003).

ADDRESSES: 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 [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. It is also available on the Internet at http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
4226.

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-
4226; 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 AD, the regulatory evaluation, any comments received, and 
other information. The address for the Docket Office (telephone 800-
647-5527) is 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 20590.

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 to supersede AD 2003-25-07, Amendment 39-13390 (68 FR 70431, 
December 18, 2003) (``AD 2003-25-07''); and AD 2005-13-39, Amendment

[[Page 55359]]

39-14176 (70 FR 38580, July 5, 2005) (``AD 2005-13-39'').
    AD 2003-25-07 applied to certain Airbus Model A319 and A320 series 
airplanes, and AD 2005-13-39 applied to certain Airbus Model A321 
series airplanes. The NPRM published in the Federal Register on March 
17, 2016 (81 FR 14404). The NPRM was prompted by a determination that 
new ELAC standards must be incorporated. The ELAC standards have been 
upgraded to version L97+, which implements enhanced AOA monitoring to 
better detect AOA blockage, including multiple AOA blockages.
    The NPRM proposed to require replacing existing ELACs with new 
ELACs having L97+ standards or revising the software in an existing 
ELAC to the L97+ standards, as applicable, which would terminate the 
requirements of AD 2003-25-07 and AD 2005-13-39. We are issuing this AD 
to prevent inadvertent activation of the AOA protections. Inadvertent 
activation of the AOA protections could result in a continuous nose-
down pitch rate that could result in reduced controllability of 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 2015-0088R1, including Appendix 01, dated June 
2, 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:

    The latest elevator aileron computer (ELAC) standard, L97+, 
implements enhanced Angle of Attack (AOA) monitoring in order to 
better detect cases of AOA blockage, including multiple AOA 
blockage.
    Two ELAC L97+ versions are currently available, Part Number (P/
N) 3945129109 with data loading capability, and P/N 3945128215 
without the data loading capability. Three existing [EASA] ADs 
requiring installation of earlier ELAC (software) have been 
identified and taken into account for cancellation by this new 
[EASA] AD.
    For the reasons described above, EASA issued AD 2015-0088, 
cancelling DGAC [Direction G[eacute]n[eacute]rale de l'Aviation 
Civile] France AD 95-203-072 (no requirements retained) [which 
corresponds to FAA AD 98-09-18, Amendment 39-10499 (63 FR 23374, 
April 29, 1998)], and partially retaining the requirements of DGAC 
France AD 2001-508 [which corresponds to FAA AD 2003-25-07], and 
[DGAC France] AD F-2004-147 (EASA approval ref. 2004-8601) [which 
corresponds to FAA AD 2005-13-39], which were superseded, and to 
require replacement of all ELAC with ELAC L97+ standard.
    Since that [EASA] AD was issued, some errors were detected in 
Appendix 1 of the [EASA] AD, and one P/N ELAC was inadvertently 
omitted. This [EASA] AD revises EASA AD 2015-0088 to correct these 
errors and to add clarification to paragraph (7) [of the EASA AD].

    The required actions include either replacing existing ELACs with 
new ELACs having L97+ standards uploaded, or revising the software in 
the existing ELACs to L97+ standards. This AD also expands the 
applicability to include all Airbus Model A318, A319, A320, and A321 
series airplanes. 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-2016-4226.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter supported 
the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for 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.

Related Service Information Under 1 CFR Part 51

    Airbus has issued Service Bulletin A320-27-1243, including Appendix 
01, dated March 17, 2015. This service information describes procedures 
for replacing the existing ELACs with new ELACs having L97+ standards, 
and modifying existing ELACs into units with L97+ standards.
    Airbus has also issued Service Bulletin A320-27-1244, dated March 
5, 2015. This service information describes procedures for modification 
of an airplane by replacing any existing ELAC unit with an ELAC 97+ 
unit having P/N 3945128215.
    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.

Costs of Compliance

    We estimate that this AD affects 940 airplanes of U.S. registry.
    The actions required by AD 2003-25-07 and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that were required by AD 2003-25-07 is $85 per product.
    The actions required by AD 2005-13-39 and retained in this AD take 
about 1 work-hour per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that were required by AD 2005-13-39 is $85 per product.
    We also estimate that it will take about 3 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 $7,230 per 
product. Based on these figures, we estimate the cost of this AD on 
U.S. operators to be $7,035,900, or $7,485 per product.
    According to the parts manufacturer, some of the costs of this AD 
may 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;

[[Page 55360]]

    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.

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:
0
a. Removing Airworthiness Directive (AD) 2003-25-07, Amendment 39-13390 
(68 FR 70431, December 18, 2003); and AD 2005-13-39, Amendment 39-14176 
(70 FR 38580, July 5, 2005); and
0
b. Adding the following new AD:

2016-17-03 Airbus: Docket No. FAA-2016-4226; Directorate Identifier 
2015-NM-095-AD.

(a) Effective Date

    This AD is effective September 23, 2016.

(b) Affected ADs

    This AD replaces the ADs identified in paragraphs (b)(1) and 
(b)(2) of this AD.
    (1) AD 2003-25-07, Amendment 39-13390 (68 FR 70431, December 18, 
2003) (``AD 2003-25-07'').
    (2) AD 2005-13-39, Amendment 39-14176 (70 FR 38580, July 5, 
2005) (``AD 2005-13-39'').

(c) Applicability

    This AD applies to the 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 27, Flight 
Controls.

(e) Reason

    This AD was prompted by a determination that new elevator 
aileron computer (ELAC) standards must be incorporated. The ELAC 
standards have been upgraded to version L97+, which implements 
enhanced angle-of-attack (AOA) monitoring to better detect AOA 
blockage, including multiple AOA blockages. We are issuing this AD 
to prevent inadvertent activation of the AOA protections. 
Inadvertent activation of the AOA protections could result in a 
continuous nose-down pitch rate that could result in reduced 
controllability of the airplane.

(f) Compliance

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

(g) Retained Replacement of ELAC L80 Units With L81 Units, With No 
Changes

    For Model A319 and A320 series airplanes, equipped with ELAC L80 
standards having part numbers listed in Airbus Service Bulletin 
A320-27-1135, dated June 29, 2001: This paragraph restates the 
requirements of paragraph (b) of AD 2003-25-07, with no changes. 
Within 1 year after January 22, 2004 (the effective date of AD 2003-
25-07): Replace both ELACs having L80 standards with new ELACs 
having L81 standards, by doing all the actions per paragraphs A., 
B., C., and D. of the Accomplishment Instructions of Airbus Service 
Bulletin A320-27-1135, dated June 29, 2001.

(h) Retained Installation of ELAC L83 or L91 Software, With No Changes

    For Model A321-111, -112, -131, -211, and -231 airplanes, except 
those with Airbus Modification 34043 installed in production: This 
paragraph restates the requirements of paragraph (g) of AD 2005-13-
39, with no changes. Within 16 months after August 9, 2005 (the 
effective date of AD 2005-13-39): Replace existing ELACs with ELACs 
having L83 standards, by accomplishing all of the actions specified 
in the Accomplishment Instructions of Airbus Service Bulletin A320-
27-1151, dated March 9, 2004, including Appendix 01, dated March 9, 
2004; or with ELACs having L91 standards, by accomplishing all of 
the actions specified in the Accomplishment Instructions of Airbus 
Service Bulletin A320-27-1152, dated June 4, 2004, including 
Appendix 01, dated June 4, 2004; as applicable.

(i) New Requirement of This AD: ELAC Replacement or Modification

    At the applicable times specified in table 1 to paragraphs (i) 
and (m)(3)(ii) of this AD: Replace each ELAC unit with an ELAC L97+ 
unit having part number (P/N) 3945129100 and software having P/N 
3945129109, or modify existing ELAC units into ELAC L97+ units 
having P/N 3945129100 with L97+ operational software P/N 3945129109 
loaded, as applicable, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-27-1243, including 
Appendix 01, dated March 17, 2015. Accomplishing this replacement 
terminates the actions required by paragraphs (g) and (h) of this 
AD.

  Table 1 to Paragraphs (i) and (m)(3)(ii) of This AD--Compliance Times
------------------------------------------------------------------------
                                           Compliance time (after the
        Airbus airplane models             effective date of this AD)
------------------------------------------------------------------------
Model A318 series airplanes with UTAS   Within 5 months.
 (formerly Goodrich) AOA P/N 0861ED or
 P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A319 series airplanes with UTAS   Within 10 months.
 (formerly Goodrich) AOA P/N 0861ED or
 P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A320 series airplanes with UTAS   Within 10 months.
 (formerly Goodrich) AOA P/N 0861ED or
 P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A321 series airplanes with UTAS   Within 5 months.
 (formerly Goodrich) AOA P/N 0861ED or
 P/N 0861ED2 installed in all 3
 positions (captain, first officer,
 and standby).
Model A318, A319, A320, and A321        Within 25 months.
 series airplanes that do not have
 UTAS (formerly Goodrich) AOA P/N
 0861ED or P/N 0861ED2 installed in
 all 3 positions (captain, first
 officer, and standby).
------------------------------------------------------------------------

(j) Optional Method of Compliance

    Modification of an airplane by replacing any existing ELAC unit 
with an ELAC 97+ unit having P/N 3945128215, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-27-1244, 
dated March 5, 2015, is an acceptable method of compliance for the 
requirements of paragraph (i) of this AD, for only that modified 
airplane. Accomplishing this modification terminates the actions 
required by paragraphs (g) and (h) of this AD for that modified 
airplane.

    Note 1 to paragraph (j) of this AD:  ELAC unit P/N 3945128215 is 
not data-loadable,

[[Page 55361]]

but it is fully interchangeable and mixable with data-loadable ELAC 
97+ unit P/N 3945129100 with software P/N 3945129109 loaded.

(k) Airplanes Excluded From Requirements of Paragraphs (g), (h), and 
(i), and From the Actions in Paragraph (j) of This AD

    Airplanes on which Airbus Modification 156546 (installation of 
ELAC L97+ with software P/N 3945129109) was installed in production 
are excluded from the requirements of paragraphs (g), (h), and (i) 
of this AD, and from the actions specified in paragraph (j) of this 
AD, provided it can be determined that no ELAC having a part number 
identified in table 2 to paragraphs (k) and (m) of this AD has been 
installed on that airplane since the date of issuance of the 
original airworthiness certificate or the date of issuance of the 
original export certificate of airworthiness.

   Table 2 to Paragraphs (k) and (m) of This AD--Prohibited ELAC Part
                                 Numbers
------------------------------------------------------------------------
          Part No.                 Designation               FIN
------------------------------------------------------------------------
3945122202..................  ELAC A320-111 Type    2 CE 1/2
                               Def..
3945122203..................  ELAC L50C...........  2 CE 1/2
3945122303..................  ELAC L50C...........  2 CE 1/2
3945122304..................  ELAC L60............  2 CE 1/2
3945122305..................  ELAC L61B...........  2 CE 1/2
3945122306..................  ELAC L61F...........  2 CE 1/2
3945122307..................  ELAC L62C...........  2 CE 1/2
C12370AA01..................  ELAC L68C...........  2 CE 1/2
3945122501..................  ELAC L69............  2 CE 1/2
3945122502..................  ELAC L69J...........  2 CE 1/2
3945122503..................  ELAC L77............  2 CE 1/2
3945122504..................  ELAC L78............  2 CE 1/2
3945122505..................  ELAC A L80..........  2 CE 1/2
3945123505..................  ELAC A' L80.........  2 CE 1/2
3945128101..................  ELAC B L80..........  2 CE 1/2
3945122506..................  ELAC A L81..........  2 CE 1/2
3945123506..................  ELAC A' L81.........  2 CE 1/2
3945128102..................  ELAC B L81..........  2 CE 1/2
3945122507..................  ELAC A L82..........  2 CE 1/2
3945123507..................  ELAC A' L82.........  2 CE 1/2
3945128103..................  ELAC B L82..........  2 CE 1/2
3945122608..................  ELAC A L83..........  2 CE 1/2
3945123608..................  ELAC A' L83.........  2 CE 1/2
3945122609..................  ELAC A L84..........  2 CE 1/2
3945123609..................  ELAC A' L84.........  2 CE 1/2
3945128204..................  ELAC B L90L.........  2 CE 1/2
3945128205..................  ELAC B L90N.........  2 CE 1/2
3945128206..................  ELAC B L91..........  2 CE 1/2
3945129101..................  ELAC B L91 data       2 CE 1/2 SW1
                               loadable.
3945128207..................  ELAC B L92..........  2 CE 1/2
3945128208..................  ELAC B L92L.........  2 CE 1/2
3945128209..................  ELAC B L93..........  2 CE 1/2
3945129103..................  ELAC B L93 data       2 CE 1/2 SW1
                               loadable.
3945128210..................  ELAC B L94..........  2 CE 1/2
3945129104..................  ELAC B L94 data       2 CE 1/2 SW1
                               loadable.
3945128212..................  ELAC B L96..........  2 CE 1/2
3945129106..................  ELAC B L96 data       2 CE 1/2 SW1
                               loadable.
3945129107..................  ELAC B L96 H-A data   2 CE 1/2 SW1
                               loadable.
3945128214..................  ELAC B L97..........  2 CE 1/2
3945129108..................  ELAC B L97 data       2 CE 1/2 SW1
                               loadable.
------------------------------------------------------------------------

(l) Later-Approved Parts

    Installation of an ELAC version (part number) approved after the 
effective date of this AD is an approved method of compliance with 
the requirements of paragraph (i) of this AD, and the actions 
specified in paragraph (j) of this AD, provided the requirements 
specified in paragraphs (l)(1) and (l)(2) of this AD are met.
    (1) The version (part number) must be 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).
    (2) The installation must be done using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the EASA; or Airbus's EASA DOA.

(m) Parts Installation Limitation

    As of the applicable time specified in paragraph (m)(1) or 
(m)(2) of this AD, do not install on any airplane an ELAC unit 
having a part number identified in table 2 to paragraphs (k) and (m) 
of this AD, except as specified in paragraph (m)(3) of this AD.
    (1) For an airplane that, as of the effective date of this AD, 
has any ELAC unit installed having a part number identified in table 
2 to paragraphs (k) and (m) of this AD: After modification of that 
airplane as required by paragraph (i) of this AD, or as specified in 
paragraph (j) of this AD.
    (2) For an airplane that, as of the effective date of this AD, 
does not have any ELAC unit installed having a part number 
identified in table 2 to paragraphs (k) and (m) of this AD: As of 
the effective date of this AD.
    (3) As of the effective date of this AD, a data-loadable ELAC B 
unit having a part number identified in table 2 to paragraphs (k) 
and (m) of this AD can be installed on an airplane provided that 
L97+ software P/N 3945129109 is uploaded at the applicable time 
specified in paragraph (m)(3)(i) or (m)(3)(ii) of this AD.
    (i) For all airplanes except those identified in paragraph 
(m)(3)(ii) of this AD: Before further flight after the ELAC B unit 
installation.
    (ii) For airplanes that have not been modified as required by 
paragraph (i) of this AD: Within the applicable compliance time

[[Page 55362]]

specified in table 1 to paragraphs (i) and (m)(3)(ii) 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, 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: [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.
    (ii) AMOCs approved previously for AD 2003-25-07 are approved as 
AMOCs for the corresponding provisions of paragraph (g) of this AD.
    (iii) AMOCs approved previously for AD 2005-13-39 are approved 
as AMOCs for the corresponding provisions of paragraph (h) 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 the EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.
    (3) Required for Compliance (RC): 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.

(o) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA Airworthiness Directive 2015-0088R1, including Appendix 01, 
dated June 2, 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-2016-4226.

(p) 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.
    (3) The following service information was approved for IBR on 
September 23, 2016.
    (i) Airbus Service Bulletin A320-27-1243, including Appendix 01, 
dated March 17, 2015.
    (ii) Airbus Service Bulletin A320-27-1244, dated March 5, 2015.
    (4) The following service information was approved for IBR on 
August 9, 2005 (70 FR 38580, July 5, 2005).
    (i) Airbus Service Bulletin A320-27-1151, including Appendix 01, 
dated March 9, 2004.
    (ii) Airbus Service Bulletin A320-27-1152, including Appendix 
01, dated June 4, 2004.
    (5) The following service information was approved for IBR on 
January 22, 2004 (68 FR 70431, December 18, 2003).
    (i) Airbus Service Bulletin A320-27-1135, dated June 29, 2001.
    (ii) Reserved.
    (6) 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.
    (7) 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.
    (8) 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.

    Issued in Renton, Washington, on August 8, 2016.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-19486 Filed 8-18-16; 8:45 am]
 BILLING CODE 4910-13-P