AD 2017-14-11

[Federal Register Volume 82, Number 135 (Monday, July 17, 2017)]
[Rules and Regulations]
[Pages 32622-32626]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-14469]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-9567; Directorate Identifier 2016-NM-147-AD; 
Amendment 39-18955; AD 2017-14-11]
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) 2007-13-08, 
for certain Airbus Model A318, A319, A320, and A321 series airplanes. 
AD 2007-13-08 required repetitive inspections of the auxiliary power 
unit (APU) starter motor, APU inlet plenum, and APU air intake for 
discrepancies; repetitive cleaning of the APU air intake; and 
applicable corrective actions. This AD expands the applicability of AD 
2007-13-08, and includes an optional terminating installation for the 
repetitive actions. This AD was prompted by a determination that the 
unsafe condition could occur on additional airplanes. We are issuing 
this AD to address the unsafe condition on these products.

DATES: This AD is effective August 21, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of August 21, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of July 
25, 2007 (72 FR 33877, June 20, 2007).

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: account.airworth-eas@

[[Page 32623]]

airbus.com; Internet: <a href="http://www.airbus.com">http://www.airbus.com</a>. 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 <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2016-9567.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2016-
9567; 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 2007-13-08, Amendment 39-15112 (72 FR 33877, 
June 20, 2007) (``AD 2007-13-08''). AD 2007-13-08 applied to certain 
Airbus Model A318, A319, A320, and A321 series airplanes. The NPRM 
published in the Federal Register on January 6, 2017 (82 FR 1623). The 
NPRM was prompted by a determination that the unsafe condition could 
occur on additional airplanes. The NPRM proposed to continue to require 
repetitive inspections of the APU starter motor, APU inlet plenum, and 
APU air intake for discrepancies; repetitive cleaning of the APU air 
intake; and applicable corrective actions. We are issuing this AD to 
detect and correct reverse flow during APU startup, which could lead to 
flame propagation in the APU air inlet and intake duct. Such conditions 
could result in an in-flight fire in the APU area.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2016-0176, dated August 31, 2016; corrected September 1, 2016 (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 airplanes. The MCAI states:

    An operator reported black smoke at the rear of the fuselage 
during taxi after landing. The smoke was caused by a fire in the 
auxiliary power unit (APU) air intake. The subsequent analysis 
demonstrated that, following numerous unsuccessful APU start 
attempts in flight, there is a risk of reverse flow leading to flame 
propagation to the APU air inlet and air intake duct.
    This condition, if not detected and corrected, could result in 
an in-flight fire in the APU area.
    Prompted by these findings, Airbus issued Service Bulletin (SB) 
A320-49-1068 to provide inspection and cleaning instructions. The 
applicable Flight Crew Operating Manual (FCOM) already contained a 
limitation for the number of APU start attempts, as follows:

APU STARTER
After 3 starter motor duty cycles, wait 60 minutes before attempting 
3 more cycles

    To address this potential unsafe condition, EASA issued AD 2006-
0153 to require repetitive inspections of the APU starter motor, APU 
inlet plenum and APU air intake [for discrepancies], as well as 
repetitive cleaning of the APU air intake [and applicable corrective 
actions].
    As the reverse flow inside the APU can only occur in flight with 
the APU inlet closed, various modifications (mod) were developed to 
introduce a new electronic control box (ECB) with associated 
software, the functionality of which keeps the APU inlet door open 
for 15 minutes, following an APU auto-shutdown in flight. 
Consequently, AD 2006-0153 [which corresponds to FAA AD 2007-13-08], 
was revised reducing the Applicability by excluding certain post-mod 
aeroplanes, and introducing these modifications as optional 
terminating actions.
    After EASA AD 2006-0153R2 was issued, it was determined that, as 
an APU ECB can be replaced (or moved from one aeroplane to another) 
in service, inadvertently installing a pre-mod ECB would reintroduce 
the unsafe condition. Prompted by this finding, EASA issued AD 2016-
0159, retaining the requirements of EASA AD 2006-0153R2, which was 
superseded, expanding the Applicability and including references to 
additional optional terminating actions.
    Since EASA AD 2016-0159 was issued, it was determined that 
paragraph (5) of the [EASA] AD contained some erroneous statements, 
inadvertently excluding certain aeroplanes, those that have Airbus 
mod 23698 or mod 24498 embodied in production, from the repetitive 
actions.
    For the reason described above, this [EASA] AD retains the 
requirements of EASA AD 2016-0159, which is superseded, and corrects 
paragraph (5). For post-mod aeroplanes where, inadvertently, an 
`affected' ECB has been installed in service, this AD adds the 
requirement to restore those aeroplanes to post-mod configuration by 
installation of a `serviceable' ECB. This [EASA] AD also introduces 
some editorial changes, not affecting the required actions.
    This [EASA] AD is republished as it was determined that one 
`affected' and one `non-affected' ECB were inadvertently omitted in 
the Tables.

    Discrepancies include a defective APU starter motor, misaligned 
brush wear indicator-pin, oil contamination of the brush wear 
indicator, and dirt, debris, dust, sand, oil, combustible residues, 
grease and other contaminations of the APU inlet plenum. Corrective 
actions include replacement of the APU starter motor and cleaning the 
APU air intake, if necessary. You may examine the MCAI in the AD docket 
on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and 
locating Docket No. FAA-2016-9567.

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.

Support for the NPRM

    United Airlines and Air Line Pilots Association, International, 
stated their support for the content of the NPRM.

Request To Include Missing Part Number

    Airbus asked that electronic control box (ECB) part number (P/N) 
3888394-230300 for APU GTCP36-300 be added to table 1 to paragraph (g) 
of the proposed AD. Airbus stated that the part number is missing in 
the table.
    We agree with the commenter's request. We have added ECB P/N 
3888394-230300 for APU GTCP36-300 to table 1 to paragraphs (g), (h), 
(i)(2)(ii), (j), and (k) of this AD. That part number was omitted from 
EASA AD 2016-0176, dated August 31, 2016; however, EASA issued a 
correction, which added that part number, on September 1, 2016. We have 
also included the corrected EASA AD in this final rule.

Request To Provide Retrofit Installation Method and Interchangeability 
Information

    Virgin America asked that the proposed AD requirements provide an 
approved retrofit installation method for P/N 3888394-321206. Virgin 
America also asked that the proposed AD requirements clearly state the 
interchangeability or lack of

[[Page 32624]]

interchangeability for the part numbers identified in table 2 of the 
proposed AD.
    Virgin America stated that it receives the Airbus Illustrated Parts 
Catalog (IPC) on a quarterly basis, which it regularly corrects to 
remove interchangeability. Virgin America added that in addition to 
correcting the IPC every quarter, it has repeatedly requested that 
Airbus Airworthiness and Engineering synchronize their viewpoint of how 
the IPC is intended to be utilized by operators. Virgin America noted 
that since EASA has corresponding ADs, it would mean that no ECB can be 
considered ``interchangeable'' by Airbus, since accomplishing a service 
bulletin is not the same as accomplishing an airplane maintenance 
manual. Virgin America requested this coordination within Airbus, both 
from an ever increasing manpower requirement (i.e., the more ADs, the 
more IPCs that need interchangeability monitored and removed quarterly) 
and also from a parts support request, since some parts providers use 
the IPC as the means to pool and issue parts. Virgin America concluded 
that a separate pool of non-interchangeable parts adds significantly to 
the cost impact of the proposed AD.
    We acknowledge the commenter's concerns; however, an approved 
retrofit installation method and interchangeability of part numbers are 
not addressed by this AD. While there might be merit to the commenter's 
suggestions, this AD is not the appropriate document in which to 
evaluate those suggestions. Therefore, we have not changed this AD in 
this regard.

Conclusion

    We reviewed the available data, including 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 changes:
    <bullet> Are consistent with the intent that was proposed in the 
NPRM for correcting the unsafe condition; and
    <bullet> 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 the following service information, which 
describes procedures for replacing the ECB. These documents are 
distinct since they apply to different airplane models in different 
configurations.
    <bullet> Airbus Service Bulletin A320-49-1077, Revision 04, dated 
February 27, 2013.
    <bullet> Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
    <bullet> Airbus Service Bulletin A320-49-1102, dated January 3, 
2012.
    <bullet> Airbus Service Bulletin A320-49-1107, Revision 02, dated 
May 10, 2016.
    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 1,182 airplanes of U.S. registry.
    The actions required by AD 2007-13-08, and retained in this 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 2007-13-08 is $340 per product.
    We also estimate that it will take about 4 work-hours per product 
to comply with the basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD on U.S. operators to be $401,880, or $340 per product.
    We have received no definitive data that will enable us to provide 
cost estimates for the on-condition actions specified in this AD.

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.

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 removing Airworthiness Directive (AD) 
2007-13-08, Amendment 39-15112 (72 FR 33877, June 20, 2007), and adding 
the following new AD:

2017-14-11 Airbus: Amendment 39-18955; Docket No. FAA-2016-9567; 
Directorate Identifier 2016-NM-147-AD.

(a) Effective Date

    This AD is effective August 21, 2017.

(b) Affected ADs

    This AD replaces AD 2007-13-08, Amendment 39-15112 (72 FR 33877, 
June 20, 2007) (``AD 2007-13-08'').

(c) Applicability

    This AD applies to Airbus airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), and (c)(4) of this AD, all manufacturer 
serial numbers, certificated in any category.
    (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 49, Airborne 
Auxiliary Power.

[[Page 32625]]

(e) Reason

    This AD was prompted by a report of a fire in the auxiliary 
power unit (APU) air intake. An analysis demonstrated that, 
following numerous unsuccessful APU start attempts in flight, there 
is a risk of reverse flow, which could lead to flame propagation to 
the APU air inlet and air intake duct. This AD was also prompted by 
the determination that AD 2007-13-08 only addresses the unsafe 
condition for certain airplanes. We are issuing this AD to detect 
and correct reverse flow during APU startup, which could lead to 
flame propagation in the APU air inlet and intake duct. Such 
conditions could result in an in-flight fire in the APU area.

(f) Compliance

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

(g) Repetitive Inspections and Corrective Actions

    Except as provided by paragraph (i) of this AD, within 600 
flight hours after July 25, 2007 (the effective date of AD 2007-13-
08), or within 60 days after the effective date of this AD, 
whichever occurs later: Inspect the APU starter motor, APU air inlet 
plenum, and APU air intake of each affected APU identified in table 
1 to paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD for 
discrepancies; and do all applicable corrective actions before 
further flight; in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-49-1068, Revision 01, dated February 
2, 2006. Repeat the inspection thereafter at intervals not to exceed 
600 flight hours.

  Table 1 to Paragraphs (g), (h), (i)(2)(ii), (j), and (k) of This AD--
                            Affected APU and
                      Electronic Control Box (ECB)
------------------------------------------------------------------------
                APU                          ECB part Nos. (P/N)
------------------------------------------------------------------------
APIC APS 3200.....................  4500003D, 4500003E, 4500003F,
                                     4500003G, 4500003H, or 4500003J.
Honeywell 131-9A..................  3888394-120201, 3888394-121202,
                                     3888394-121203, 3888394-221202, or
                                     3888394-221203.
Honeywell GTCP36-300..............  307950-1, 307950-2, 307950-3, 307950-
                                     4, 304640-1, 304640-2, 304640-3,
                                     304640-4, 304817-1, 304817-2, or
                                     3888394-230300.
------------------------------------------------------------------------

(h) Repetitive Cleanings

    Except as provided by paragraph (i) of this AD, prior to the 
accumulation of 2,400 flight hours since first flight of the 
airplane, or within 600 flight hours after July 25, 2007 (the 
effective date of AD 2007-13-08), or within 60 days after the 
effective date of this AD, whichever occurs latest, unless 
accomplished previously in accordance with Airbus Service Bulletin 
A320-49-1098, dated June 21, 2011: Clean the APU air intake of each 
affected APU identified in table 1 to paragraphs (g), (h), 
(i)(2)(ii), (j), and (k) of this AD, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-49-1068, 
Revision 01, dated February 2, 2006. Repeat the cleaning task 
thereafter at intervals not to exceed 2,400 flight hours.

(i) Exceptions to Requirements in Paragraphs (g) and (h) of This AD

    (1) For airplanes equipped with an APU and associated ECB part 
number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), and 
(j) of this AD, the actions specified in paragraphs (g) and (h) of 
this AD are not required.

   Table 2 to Paragraphs (i)(1), (i)(2)(ii), and (j) of This AD--Non-
                              Affected ECB
------------------------------------------------------------------------
                APU                          ECB Part Nos. (P/N)
------------------------------------------------------------------------
APIC APS 3200.....................  4500003K, 4500003L, or 4500003M.
Honeywell 131-9A..................  3888394-121204, 3888394-121205,
                                     3888394-221204, 3888394-221205, or
                                     3888394-321206.
Honeywell GTCP36-300..............  304640-5, 304817-3, or 3888394-
                                     230301.
------------------------------------------------------------------------

    (2) For airplanes on which Airbus Modification 35803, 35936, 
152289, 152645, 155015, or 157848 has been embodied in production, 
the actions specified in paragraphs (g) and (h) of this AD are not 
required provided that, within 30 days after the effective date of 
this AD, the applicable actions specified in paragraphs (i)(2)(i) 
and (i)(2)(ii) of this AD are done.
    (i) The part number of the installed ECB is identified.
    (ii) Any affected ECB identified in table 1 to paragraphs (g), 
(h), (i)(2)(ii), (j), and (k) of this AD that is found to be 
installed is replaced with an ECB having a part number identified in 
table 2 to paragraphs (i)(1), (i)(2)(ii), and (j) of this AD, as 
applicable to the APU installed on the airplane; and the replacement 
is done in accordance with the Accomplishment Instructions of the 
applicable service information identified in paragraph 
(i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), (i)(2)(ii)(D), 
(i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD; or 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).
    (A) Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
    (B) Airbus Service Bulletin A320-49-1075, Revision 01, dated 
December 1, 2006.
    (C) Airbus Service Bulletin A320-49-1077, Revision 04, dated 
February 27, 2013.
    (D) Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
    (E) Airbus Service Bulletin A320-49-1102, dated January 3, 2012.
    (F) Airbus Service Bulletin A320-49-1107, Revision 02, dated May 
10, 2016.
    (3) For airplanes on which an APU ECB having a part number 
approved after the effective date of this AD is installed, the 
actions specified in paragraphs (g) and (h) of this AD are not 
required, provided the conditions specified in paragraphs (i)(3)(i) 
and (i)(3)(ii) of this AD are met.
    (i) The part number must be approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.
    (ii) The installation must be accomplished in accordance with 
airplane modification instructions approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or EASA; or Airbus's EASA DOA.

(j) Optional Terminating Action

    Replacing an affected ECB identified in table 1 to paragraphs 
(g), (h), (i)(2)(ii), (j), and (k) of this AD with an ECB having a 
part number identified in table 2 to paragraphs (i)(1), (i)(2)(ii), 
and (j) of this AD, as applicable to the APU installed on the 
airplane, constitutes terminating action for the repetitive 
inspections required by paragraphs (g) and (h) of this AD. The 
replacement must be done in accordance with the Accomplishment 
Instructions of the applicable service information identified in 
paragraph (i)(2)(ii)(A), (i)(2)(ii)(B), (i)(2)(ii)(C), 
(i)(2)(ii)(D), (i)(2)(ii)(E), or (i)(2)(ii)(F) of this AD, or using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Parts Installation Prohibition

    As of the effective date of this AD, no person may install on 
any airplane an APU with an associated ECB identified in table 1 to 
paragraphs (g), (h), (i)(2)(ii), (j), and (k) of this AD.

[[Page 32626]]

(l) Credit for Previous Actions

    This paragraph provides credit for actions specified in 
paragraphs (i)(2) and (j) of this AD, if those actions were 
performed before the effective date of this AD using any of the 
service information specified in paragraphs (l)(1) through (l)(7) of 
this AD.
    (1) Airbus Service Bulletin A320-49-1075, dated September 22, 
2006, which was incorporated by reference in AD 2007-13-08.
    (2) Airbus Service Bulletin A320-49-1077, dated March 21, 2007, 
which is not incorporated by reference in this AD.
    (3) Airbus Service Bulletin A320-49-1077, Revision 01, dated 
August 9, 2007, which is not incorporated by reference in this AD.
    (4) Airbus Service Bulletin A320-49-1077, Revision 02, dated 
July 1, 2008, which is not incorporated by reference in this AD.
    (5) Airbus Service Bulletin A320-49-1077, Revision 03, dated 
December 8, 2008, which is not incorporated by reference in this AD.
    (6) Airbus Service Bulletin A320-49-1107, dated November 5, 
2013, which is not incorporated by reference in this AD.
    (7) Airbus Service Bulletin A320-49-1107, Revision 01, dated 
July 28, 2015, which is not incorporated by reference in this AD.

(m) 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 manager of the International Branch, send it to the 
attention of the person identified in paragraph (n)(2) of this AD. 
Information may be emailed to: <a href="/cdn-cgi/l/email-protection#0d34204c4340203c3c3b204c40424e205f485c58485e595e4d6b6c6c236a627b"><span class="__cf_email__" data-cfemail="221b0f636c6f0f1313140f636f6d610f7067737767717671624443430c454d54">[email&#160;protected]</span></a>.
    (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 for AD 2007-13-08 are approved as 
AMOCs for the corresponding provisions of paragraphs (g) and (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 EASA; or Airbus's EASA DOA. If 
approved by the DOA, the approval must include the DOA-authorized 
signature.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2016-0176, dated August 31, 2016; corrected September 
1, 2016, for related information. This MCAI may be found in the AD 
docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching 
for and locating Docket No. FAA-2016-9567.
    (2) For more information about this AD, 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.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(5) and (o)(6) of this AD.

(o) 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 
August 21, 2017.
    (i) Airbus Service Bulletin A320-49-1077, Revision 04, dated 
February 27, 2013.
    (ii) Airbus Service Bulletin A320-49-1098, dated June 21, 2011.
    (iii) Airbus Service Bulletin A320-49-1102, dated January 3, 
2012.
    (iv) Airbus Service Bulletin A320-49-1107, Revision 02, dated 
May 10, 2016.
    (4) The following service information was approved for IBR on 
July 25, 2007 (72 FR 33877, June 20, 2007).
    (i) Airbus Service Bulletin A320-49-1068, Revision 01, dated 
February 2, 2006.
    (ii) Airbus Service Bulletin A320-49-1070, dated July 28, 2006.
    (iii) Airbus Service Bulletin A320-49-1075, Revision 01, dated 
December 1, 2006.
    (5) 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: <a href="/cdn-cgi/l/email-protection#78191b1b170d160c5619110a0f170a0c10551d190b3819110a1a0d0b561b1715"><span class="__cf_email__" data-cfemail="7e1f1d1d110b100a501f170c09110c0a16531b1f0d3e1f170c1c0b0d501d1113">[email&#160;protected]</span></a>; Internet: 
<a href="http://www.airbus.com">http://www.airbus.com</a>.
    (6) 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.
    (7) 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: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on June 29, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-14469 Filed 7-14-17; 8:45 am]
BILLING CODE 4910-13-P