AD 2016-07-30

[Federal Register Volume 81, Number 71 (Wednesday, April 13, 2016)]
[Rules and Regulations]
[Pages 21722-21726]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2016-08267]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2015-4810; Directorate Identifier 2015-NM-090-AD; 
Amendment 39-18475; AD 2016-07-30]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for all 
Airbus Model A330-200, -200 Freighter, and -300 series airplanes, and 
all Airbus Model A340-200, -300, -500, and -600 series airplanes. This 
AD was prompted by a report of blockage of Angle of Attack (AOA) probes 
during climb, leading to activation of the Alpha Protection (Alpha 
Prot) while the Mach number increased. This activation could cause a 
continuous nose-down pitch rate that cannot be stopped with backward 
sidestick input, even in the full backward position. For certain 
airplanes, this AD requires replacing certain AOA sensors (probes) with

[[Page 21723]]

certain new AOA sensors. For certain other airplanes, this AD also 
requires inspections and functional heat testing of certain AOA sensors 
for discrepancies, and replacement if necessary. We are issuing this AD 
to prevent erroneous AOA information and Alpha Prot activation due to 
blocked AOA probes, which could result in a continuous nose-down 
command and loss of control of the airplane.

DATES: This AD becomes effective May 18, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 18, 2016.

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax 
+33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#ea8b83989d85989e8283848f9999c4abd9d9dac7abd9dedaaa8b8398889f99c4898587"><span class="__cf_email__" data-cfemail="d2b3bba0a5bda0a6babbbcb7a1a1fc93e1e1e2ff93e1e6e292b3bba0b0a7a1fcb1bdbf">[email&#160;protected]</span></a>; 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-2015-
4810.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov/#!docketDetail">http://www.regulations.gov/#!docketDetail</a>;D=FAA-2015-4810; 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 street address for the Docket Operations 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.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1138; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to all Airbus Model A330-200, 
-200 Freighter, and -300 series airplanes; and all Airbus Model A340-
200, -300, -500, and -600 series airplanes. The NPRM published in the 
Federal Register on November 12, 2015 (80 FR 69899) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0134, dated July 8, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for all Airbus Model 
A330-200, -200 Freighter, and -300 series airplanes; and all Model 
A340-200, -300, -500, and -600 series airplanes. The MCAI states:

    An occurrence was reported where an Airbus A321 aeroplane 
encountered a blockage of two Angle of Attack (AOA) probes during 
climb, leading to activation of the Alpha Protection (Alpha Prot) 
while the Mach number increased. The flight crew managed to regain 
full control and the flight landed uneventfully. It was determined 
that the affected AOA probes are also fitted on A330 and A340 
aeroplanes.
    When Alpha Prot is activated due to blocked AOA probes, the 
flight control laws order a continuous nose down pitch rate that, in 
a worst case scenario, cannot be stopped with backward sidestick 
inputs, even in the full backward position. If the Mach number 
increases during a nose down order, the AOA value of the Alpha Prot 
will continue to decrease. As a result, the flight control laws will 
continue to order a nose down pitch rate, even if the speed is above 
minimum selectable speed, known as VLS.
    This condition, if not corrected, could result in loss of 
control of the aeroplane.
    Investigation results indicated that aeroplanes equipped with 
certain UTC Aerospace (UTAS, formerly known as Goodrich) AOA 
sensors, or equipped with certain SEXTANT/THOMSON AOA sensors, 
appear to have a greater susceptibility to adverse environmental 
conditions than aeroplanes equipped with the latest Thales AOA 
sensor, Part Number (P/N) C16291AB, which was designed to improve 
AOA indication behaviour in heavy rain conditions.
    Having determined that replacement of these AOA sensors is 
necessary to achieve and maintain the required safety level of the 
aeroplane, EASA issued [an AD ***], to require modification of the 
aeroplanes by replacement of the affected P/N sensors, and, after 
modification, prohibits (re-) installation of those P/N AOA sensors. 
That [EASA] AD also required repetitive detailed visual inspections 
(DET) and functional heating tests of certain Thales AOA sensors and 
provided an optional terminating action for those inspections.
    Since EASA AD 2015-0089 was issued, based on further analysis 
results, Airbus issued Operators Information Transmission (OIT) Ref. 
999.0017/15 Revision 1, instructing operators to speed up the 
removal from service of UTAS P/N 0861ED2 AOA sensors.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA [AD ***], which is superseded, but reduces the 
compliance times for aeroplanes with UTAS P/N 0861ED2 AOA sensors 
installed.

    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-2015-
4810.

Actions Since the NPRM Was Issued

    Since we issued the NPRM Airbus has issued the following service 
information:
    <bullet> Service Bulletin A330-34-3215, Revision 03, dated July 23, 
2015.
    <bullet> Service Bulletin A340-34-4215, Revision 03, dated July 27, 
2015.
    <bullet> Service Bulletin A340-34-5062, Revision 02, dated July 24, 
2015.

Explanation of Certain Changes to the NPRM

    We have revised paragraph (j) of this AD to refer to this revised 
service information.
    We have also added a new paragraph (l) to this AD, and reidentified 
subsequent paragraphs, to give credit for doing the actions using the 
following service information:
    <bullet> Airbus Service Bulletin A330-34-3215, Revision 02, dated 
March 29, 2010.
    <bullet> Airbus Service Bulletin A340-34-4215, Revision 02, dated 
March 29, 2010.
    <bullet> Airbus Service Bulletin A340-34-5062, Revision 01, dated 
March 29, 2010.

Comments

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

Request To Reduce Certain Compliance Times

    Airbus asked that we reduce the compliance time from 22 months to 
12 months for P/N 0861ED removal, and from 7 months to 3 months for P/N 
0861ED2 removal.
    We do not agree with the request, as no supporting data was 
provided by the commenter. We contacted Airbus to determine if there 
was a justification for reducing the compliance times specified in the 
proposed AD. We noted that reducing the compliance times would 
necessitate (under the provisions of the Administrative Procedure Act) 
reissuing the notice, reopening the period for public comment, 
considering additional

[[Page 21724]]

comments subsequently received, and eventually issuing a final rule. 
Airbus stated it concurs with keeping the compliance times specified in 
the proposed AD. We have determined that further delay of this final 
rule is not appropriate. However, if additional data are presented that 
would justify a shorter compliance time, we may consider further 
rulemaking on this issue.
    In developing an appropriate compliance time, we considered the 
safety implications, parts availability, and normal maintenance 
schedules for timely accomplishment of replacing the AOA sensors, as 
well as the compliance times required by the EASA AD. In consideration 
of these factors, we have determined that the compliance time, as 
proposed, represents an appropriate time in which the AOA sensors can 
be replaced in a timely manner within the fleet, while still 
maintaining an adequate level of safety. Most ADs, including this one, 
permit operators to accomplish the requirements of an AD at a time 
earlier than the specified compliance time; therefore, an operator may 
choose to replace the AOA sensors earlier. We have not changed this 
final rule in this regard.

Conclusion

    We reviewed the relevant data, considered the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these minor changes:
    <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:
    <bullet> Service Bulletin A330-34-3215, Revision 03, dated July 23, 
2015.
    <bullet> Service Bulletin A330-34-3228, dated October 7, 2009.
    <bullet> Service Bulletin A330-34-3315, dated March 26, 2015.
    <bullet> Service Bulletin A340-34-4215, Revision 03, dated July 27, 
2015.
    <bullet> Service Bulletin A340-34-4234, dated October 7, 2009.
    <bullet> Service Bulletin A340-34-4294, dated March 26, 2015.
    <bullet> Service Bulletin A340-34-5062, Revision 02, dated July 24, 
2015.
    <bullet> Service Bulletin A340-34-5070, dated October 9, 2009.
    <bullet> Service Bulletin A340-34-5105, dated March 26, 2015.
    The service information describes procedures for replacing certain 
pitot probes with certain new pitot probes. The service information 
also describes procedures for inspections and functional heat testing 
of certain pitot probes, and replacement if necessary. 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 55 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                                   Cost on U.S.
              Action                      Labor cost         Parts cost       Cost per product       operators
----------------------------------------------------------------------------------------------------------------
Replacement.......................  5 work-hours x $85                 $0  $425.................         $23,375
                                     per hour = $425.
Inspection/test...................  3 work-hours x $85                  0  255 per inspection/            14,025
                                     per hour = $255.                       test cycle.
----------------------------------------------------------------------------------------------------------------

    We have received no definitive data that will enable us to provide 
a cost estimate 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 adding the following new airworthiness 
directive (AD):

2016-07-30 Airbus: Amendment 39-18475. Docket No. FAA-2015-4810; 
Directorate Identifier 2015-NM-090-AD.

(a) Effective Date

    This AD becomes effective May 18, 2016.

[[Page 21725]]

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes, certificated in any category, 
identified in paragraphs (c)(1) and (c)(2) of this AD, all 
manufacturer serial numbers.
    (1) Airbus Model A330-201, -202, -203, -223, -223F, -243, -243F, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, -313, -541, 
and -642 airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 34, Navigation.

(e) Reason

    This AD was prompted by a report of blockage of two Angle of 
Attack (AOA) probes during climb, leading to activation of the Alpha 
Protection (Alpha Prot) while the Mach number increased. This 
activation could cause a continuous nose-down pitch rate that cannot 
be stopped with backward sidestick input, even in the full backward 
position. We are issuing this AD to prevent erroneous AOA 
information and Alpha Prot activation due to blocked AOA probes, 
which could result in a continuous nose-down command and consequent 
loss of control of the airplane.

(f) Compliance

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

(g) Replacement of Certain UTC Aerospace (UTAS) AOA Sensors

    For airplanes on which any UTAS AOA sensor having part number 
(P/N) 0861ED or P/N 0861ED2 is installed: At the applicable time 
specified in paragraph (h) of this AD, replace all Captain and First 
Officer AOA sensors (probes) having P/N 0861ED or 0861ED2 with AOA 
sensors having Thales P/N C16291AB, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (g)(1), (g)(2), or (g)(3) of this AD.
    (1) Airbus Service Bulletin A330-34-3315, dated March 26, 2015 
(for Model A330 airplanes).
    (2) Airbus Service Bulletin A340-34-4294, dated March 26, 2015 
(for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5105, dated March 26, 2015 
(for Model A340-500 and -600 airplanes).

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

    Do the actions required by paragraph (g) of this AD at the 
applicable time specified in paragraph (h)(1) or (h)(2) of this AD.
    (1) For airplanes with AOA sensors having P/N 0861ED: Within 22 
months after the effective date of this AD.
    (2) For airplanes with AOA sensors having P/N 0861ED2: Within 7 
months after the effective date of this AD.

(i) Replacement of Certain SEXTANT/THOMSON AOA Sensors

    For airplanes on which any SEXTANT/THOMSON AOA sensor having P/N 
45150320 is installed: Within 22 months after the effective date of 
this AD, replace all SEXTANT/THOMSON AOA sensors (probes) having P/N 
45150320 with AOA sensors having Thales P/N C16291AB, in accordance 
with the Accomplishment Instructions of the applicable service 
information identified in paragraph (i)(1) or (i)(2) of this AD.
    (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 
(for Model A330 airplanes).
    (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 
(for Model A340-200 and -300 airplanes).

(j) Repetitive Inspections/Tests of Certain Thales AOA Sensors

    For airplanes on which one or more Thales AOA sensor having P/N 
C16291AA is installed: Before the accumulation of 17,000 total 
flight hours on the AOA sensor since first installation on an 
airplane, or within 6 months after the effective date of this AD, 
whichever occurs later; and thereafter at intervals not to exceed 
3,800 flight hours; do a detailed inspection of the three AOA 
sensors at FINs 3FP1, 3FP2, and 3FP3 for discrepancies (e.g., the 
vane of the sensor does not deice properly), and a functional 
heating test of each AOA sensor having P/N C16291AA, in accordance 
with the Accomplishment Instructions of the applicable service 
information identified in paragraph (j)(1), (j)(2), or (j)(3) of 
this AD.
    (1) Airbus Service Bulletin A330-34-3215, Revision 03, dated 
July 23, 2015 (for Model A330 airplanes).
    (2) Airbus Service Bulletin A340-34-4215, Revision 03, dated 
July 27, 2015 (for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5062, Revision 02, dated 
July 24, 2015 (for Model A340-500 and -600 airplanes).

(k) Corrective Actions

    If any discrepancy is found during any inspection required by 
paragraph (j) of this AD, or if any test is failed during the 
heating test required by paragraph (j) of this AD: Before further 
flight, replace all affected AOA sensors with sensors identified in 
paragraph (k)(1) or (k)(2) of this AD, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (j)(1), (j)(2), or (j)(3) of this AD.
    (1) Replace with AOA sensors having Thales P/N C16291AA, on 
which the inspection and test required by paragraph (j) of this AD 
were passed.
    (2) Replace with AOA sensors having Thales P/N C16291AB.

(l) Credit for Previous Actions

    This paragraph provides credit for the actions required by 
paragraph (g) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraphs (l)(1), (l)(2), and (l)(3) of this AD, which 
are not incorporated by reference in this AD.
    (1) Airbus Service Bulletin A330-34-3215, Revision 02, dated 
March 29, 2010.
    (2) Airbus Service Bulletin A340-34-4215, Revision 02, dated 
March 29, 2010.
    (3) Airbus Service Bulletin A340-34-5062, Revision 01, dated 
March 29, 2010.

(m) Airplanes Excluded From Certain Requirements

    (1) The actions specified in paragraphs (g), (i), (j), and (k) 
of this AD are not required, provided that the conditions specified 
in paragraphs (m)(1)(i), (m)(1)(ii), and (m)(1)(iii) of this AD are 
met.
    (i) Airbus Modification 58555 (installation of Thales P/N 
C16291AB AOA sensors) has been embodied in production.
    (ii) Airbus Modification 46921 (installation of UTAS AOA 
sensors) has not been embodied in production.
    (iii) No AOA sensor having SEXTANT/THOMSON P/N 45150320 or UTAS 
P/N 0861ED or P/N 0861ED2 has been installed on the airplane since 
date of issuance of the original airworthiness certificate or date 
of issuance of the original export certificate of airworthiness.
    (2) The actions specified in paragraphs (g) and (i) of this AD 
are not required, provided that all conditions specified in 
paragraphs (m)(2)(i), (m)(2)(ii), and (m)(2)(iii) of this AD are 
met.
    (i) Only AOA sensors with part numbers approved after the 
effective date of this AD have been installed.
    (ii) The AOA sensor part number is approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the European Aviation Safety Agency (EASA); or Airbus's EASA Design 
Organization Approval (DOA).
    (iii) The installation is accomplished in accordance with 
airplane modification instructions approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the EASA; or Airbus's EASA DOA.

(n) Optional Terminating Modification

    Replacement of all Thales AOA sensors having P/N C16291AA with 
Thales AOA sensors having P/N C16291AB, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraph (n)(1), (n)(2), or (n)(3) of this AD, 
terminates the repetitive inspections and functional heating tests 
required by paragraph (j) of this AD.
    (1) Airbus Service Bulletin A330-34-3228, dated October 7, 2009 
(for Model A330 airplanes).
    (2) Airbus Service Bulletin A340-34-4234, dated October 7, 2009 
(for Model A340-200 and -300 airplanes).
    (3) Airbus Service Bulletin A340-34-5070, dated October 9, 2009 
(for Model A340-500 and -600 airplanes).

(o) Parts Installation Prohibitions

    (1) For airplanes on which only Thales P/N C16291AB AOA sensors 
are installed as of the effective date of this AD: No person may 
install, on any airplane, a Thales AOA sensor having P/N C16291AA as 
of the effective date of this AD.
    (2) For airplanes on which the modification specified in 
paragraph (n) of this AD has been done: No person may install, on 
any airplane, a Thales AOA sensor

[[Page 21726]]

having P/N C16291AA after accomplishing the specified modification.
    (3) For airplanes on which Thales P/N C16291AA or P/N C16291AB 
AOA sensors are installed as of the effective date of this AD: No 
person may install, on any airplane, a UTAS AOA sensor having P/N 
0861ED or P/N 0861ED2, or a SEXTANT/THOMSON AOA sensor having P/N 
45150320, as of the effective date of this AD.
    (4) For airplanes on which the replacement required by paragraph 
(i) of this AD has been done: No person may install, on any 
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a 
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing 
the replacement.
    (5) For airplanes on which the replacement required by paragraph 
(g) of this AD has been done: No person may install, on any 
airplane, a UTAS AOA sensor having P/N 0861ED or P/N 0861ED2, or a 
SEXTANT/THOMSON AOA sensor having P/N 45150320, after accomplishing 
the replacement, except that a UTAS AOA sensor having P/N 0861ED may 
be installed in the standby position of that airplane.

(p) 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: Vladimir 
Ulyanov, Aerospace Engineer, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, 
WA 98057-3356; telephone 425-227-1138; fax 425-227-1149. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#87beaac6c9caaab6b6b1aac6cac8c4aad5c2d6d2c2d4d3d4c7e1e6e6a9e0e8f1"><span class="__cf_email__" data-cfemail="9da4b0dcd3d0b0acacabb0dcd0d2deb0cfd8ccc8d8cec9ceddfbfcfcb3faf2eb">[email&#160;protected]</span></a>. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or the 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.

(q) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0134, dated July 8, 2015, 
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-2015-4810.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (r)(3) and (r)(4) of this AD.

(r) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless this AD specifies otherwise.
    (i) Airbus Service Bulletin A330-34-3215, Revision 03, dated 
July 23, 2015.
    (ii) Airbus Service Bulletin A330-34-3228, dated October 7, 
2009.
    (iii) Airbus Service Bulletin A330-34-3315, dated March 26, 
2015.
    (iv) Airbus Service Bulletin A340-34-4215, Revision 03, dated 
July 27, 2015.
    (v) Airbus Service Bulletin A340-34-4234, dated October 7, 2009.
    (vi) Airbus Service Bulletin A340-34-4294, dated March 26, 2015.
    (vii) Airbus Service Bulletin A340-34-5062, Revision 02, dated 
July 24, 2015.
    (viii) Airbus Service Bulletin A340-34-5070, dated October 9, 
2009.
    (ix) Airbus Service Bulletin A340-34-5105, dated March 26, 2015.
    (3) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#20414952574f525448494e4553530e611313100d61131410604149524255530e434f4d"><span class="__cf_email__" data-cfemail="1879716a6f776a6c7071767d6b6b36592b2b2835592b2c285879716a7a6d6b367b7775">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <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 March 26, 2016.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-08267 Filed 4-12-16; 8:45 am]
 BILLING CODE 4910-13-P