```

[Federal Register Volume 81, Number 203 (Thursday, October 20, 2016)]
[Rules and Regulations]
[Pages 72515-72519]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-24191]

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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-0465; Directorate Identifier 2015-NM-096-AD; 
Amendment 39-18679; AD 2016-20-13]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are adopting a new airworthiness directive (AD) for certain 
Airbus Model A330-200 and -300 series airplanes; and Model A340-200 and 
-300 series airplanes. This AD was prompted by a determination that the 
compliance times for certain post-repair inspections and certain 
allowable damage limits (ADLs) must be reduced in order to address 
fatigue. This AD requires identifying any repairs and ADLs used to 
assess or control any structural damage on certain structural areas, 
and corrective action if necessary. We are issuing this AD to prevent 
fatigue damage on primary structure and structural repairs, which could 
result in reduced structural integrity of the airplane.

DATES: This AD is effective November 25, 2016.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of November 25, 
2016.

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@airbus.com; 
Internet: http://www.airbus.com. You may view this referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221. It is also available on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2016-0465.

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-
0465; 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 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: 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 certain Airbus Model A330-
200 and -300 series airplanes; and Model A340-200 and -300 series 
airplanes. The NPRM published in the Federal Register on February 18, 
2016 (81 FR 8160) (``the NPRM''). The NPRM was prompted by a 
determination that the compliance times for certain post-repair 
inspections and certain ADLs must be reduced in order to address 
fatigue. The NPRM proposed to require identifying any repairs and ADLs 
used to assess or control any structural damage on certain structural 
areas, and corrective action if necessary. We are issuing this AD to 
prevent fatigue damage on primary structure and structural repairs, 
which could result in reduced structural integrity 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 AD 
2015-0101R1, dated June 12, 2015 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the

[[Page 72516]]

MCAI''), to correct an unsafe condition for certain Airbus Model A330-
200 and -300 series airplanes; and Model A340-200 and -300 series 
airplanes. The MCAI states:

    Result of a fleet survey accomplished in 2008 identified that 
the nature of flight missions of A330 and A340-200/300 fleets had 
significantly changed in comparison with assumed usage during the 
type certification. Consequently, it was decided to recalculate the 
Structural Repair Manual (SRM) fatigue values to ensure that the 
given threshold and intervals remain valid.
    The results of this recalculation identified reduced thresholds 
and intervals applicable for repairs and Allowable Damage Limits 
(ADL) affecting the following areas:

--Door cut-out corners of door surrounding panels (forward cargo 
door, forward passenger (PAX) door, mid PAX door, emergency exit 
door/PAX door 3, aft cargo door, bulk cargo door, aft PAX door), on 
both Left Hand (LH) and Right Hand (RH) sides,
--Stringer (STGR) 9 junction between Frame (FR) 10 and FR13 on both 
LH and RH sides, and
--Fuselage skin doubler repairs on both LH and RH sides.

    Failing to apply the reduced thresholds and intervals, could 
adversely affect the structural integrity of the aeroplane.
    To address this unsafe condition, Airbus issued SRM revision 
dated April 2013 and temporary revision (TR) 53-001 for the STGR9 
junction between FR10 and FR13 area (and subsequent revisions) to 
introduce reduced thresholds and intervals for the affected ADLs and 
repairs and issued a set of Service Bulletins (SB) to identify the 
ADLs used and repairs made, as well as to enable operators to update 
aeroplane repair records.
    Consequently EASA issued AD * * *, to require identification of 
any repairs and/or ADL used to assess or control any structural 
damage on certain structural areas and, depending on findings, 
accomplishment of corrective action(s) [including revising the 
maintenance or inspection program as applicable to incorporate 
revised thresholds and intervals and repair].
    Since that [EASA] AD was issued, data review confirmed that A330 
freighter versions are not affected by the unsafe condition.
    This [EASA] AD is revised to remove A330-223F and A330-243F from 
the Applicability.

    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-
0465.

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.

Requests To Revise Paragraph (g) of the Proposed AD To Include Physical 
Inspection as Alternative to Records Check

    Delta Air Lines (DAL) and American Airlines requested that we 
revise the proposed AD to include a physical inspection of affected 
areas of the airplane in case the maintenance records are unavailable 
or inconclusive as an alternative to the records check specified in 
paragraph (g) of the proposed AD. DAL pointed out that their 
maintenance record search for applied SRM ADLs had inconclusive 
results. DAL also pointed out that other U.S. operators may not be able 
to comply with the proposed AD by performing a maintenance records 
check. American Airlines provided no further justification.
    We agree that an alternative inspection method in lieu of a 
maintenance records check could be appropriate. When the repair records 
and/or applied SRM ADL are unavailable or inconclusive, then an 
alternative method of inspection can be done 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). We have revised 
paragraph (g) of this AD to include an alternative method of inspection 
in the case of inconclusive or unavailable records.
    We have also revised paragraph (h)(2) of this AD to clarify the 
affected repairs for that paragraph.

Additional Change Made in This AD

    We have converted Tables 1 and 2 of the proposed AD into text. 
These changes are for formatting purposes only and do not change the 
intent of those requirements.

Conclusion

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

Related Service Information Under 1 CFR Part 51

    We reviewed the following Airbus service information. The service 
information describes procedures for updating the airplane repair 
records with revised thresholds and intervals. These documents are 
distinct since they apply to different airplane models in different 
configurations.
     Airbus Service Bulletin A330-53-3232, dated November 4, 
2014.
     Airbus Service Bulletin A330-53-3233, dated September 26, 
2014.
     Airbus Service Bulletin A330-53-3234, dated December 8, 
2014.
     Airbus Service Bulletin A330-53-3235, Revision 01, dated 
January 14, 2015.
     Airbus Service Bulletin A340-53-4222, dated November 25, 
2014.
     Airbus Service Bulletin A340-53-4223, dated September 26, 
2014.
     Airbus Service Bulletin A340-53-4224, dated December 15, 
2014.
     Airbus Service Bulletin A340-53-4225, Revision 01, dated 
January 14, 2015.
    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 95 airplanes of U.S. registry.
    We estimate the following costs to comply with this AD:

                                                 Estimated Costs
----------------------------------------------------------------------------------------------------------------
                                                                                    Cost per       Cost on U.S.
               Action                        Labor cost           Parts cost        product         operators
----------------------------------------------------------------------------------------------------------------
Records review......................  2 work-hours x $85 per               $0             $170          $16,150
                                       hour = $170.
----------------------------------------------------------------------------------------------------------------

[[Page 72517]]

    We have received no definitive data that would 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 adding the following new airworthiness 
directive (AD):

2016-20-13 Airbus: Amendment 39-18679. Docket No. FAA-2016-0465; 
Directorate Identifier 2015-NM-096-AD.

(a) Effective Date

    This AD is effective November 25, 2016.

(b) Affected ADs

    None.

(c) Applicability

    This AD applies to the airplanes identified in paragraphs (c)(1) 
and (c)(2) of this AD, certificated in any category, manufacturer 
serial numbers (MSNs) 1 through 1,600 inclusive.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 53, Fuselage.

(e) Reason

    This AD was prompted by a determination that the compliance 
times for certain post-repair inspections and certain allowable 
damage limits (ADLs) must be reduced in order to address fatigue. We 
are issuing this AD to prevent fatigue damage on primary structure 
and structural repairs, which could result in reduced structural 
integrity of the airplane.

(f) Compliance

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

(g) Records Review

    (1) At the applicable times in paragraphs (g)(1)(i) through 
(g)(1)(x) of this AD, review the airplane maintenance records to 
identify any structural repair manual (SRM) ADLs used to assess or 
control any structural damage or any structural repair accomplished 
as specified in an SRM, as applicable, that have been applied on the 
applicable areas as specified in paragraphs (g)(2)(i) through 
(g)(2)(iv) of this AD. If the review of the airplane maintenance 
records is inconclusive or the records are unavailable, inspect the 
airplane to identify any SRM ADL used to assess or control any 
structural damage or any structural repair accomplished in 
accordance with a SRM, as applicable, using a method approved by 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA).
    (i) For Model A330-200 pre-mod 49144 airplanes, with left-hand 
(LH) and right-hand (RH) mid passenger (PAX) door surround panels, 
as specified in Airbus Service Bulletin A330-53-3232, dated November 
4, 2014: Within 12 months after the effective date of this AD.
    (ii) For Model A330-200 pre-mod 49144 airplanes, with forward 
cargo door, emergency exit door/PAX door 3, aft cargo door, bulk 
cargo door, and aft PAX door surround panels; as specified in Airbus 
Service Bulletin A330-53-3232, dated November 4, 2014: Within 24 
months after the effective date of this AD.
    (iii) For Model A330-300 pre-mod 49144 airplanes and Model A340-
200 and -300 pre-mod 49144 airplanes, with mid PAX door surround 
panels, forward cargo door, emergency exit door/PAX door 3, aft 
cargo door, bulk cargo door, and aft PAX door surround panels; as 
specified in Airbus Service Bulletin A330-53-3232, dated November 4, 
2014; or Airbus Service Bulletin A340-53-4222, dated November 25, 
2014; as applicable: Within 24 months after the effective date of 
this AD.
    (iv) For Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 and Model A340-211, -
212, -213, -311, -312, and -313, all post-mod 40347 airplanes, with 
forward PAX door surround panels with an ADL with a temporary life 
limit; as specified in Airbus Service Bulletin A330-53-3233, dated 
September 26, 2014; or Airbus Service Bulletin A340-53-4223, dated 
September 26, 2014; as applicable: Within 12 months after the 
effective date of this AD.
    (v) For Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 and Model A340-211, -
212, -213, -311, -312, and -313, all post-mod 40347 airplanes, with 
forward PAX door surround panels with an ADL with a Permanent 
Acceptance; as specified in Airbus Service Bulletin A330-53-3233, 
dated September 26, 2014; or Airbus Service Bulletin A340-53-4223, 
dated September 26, 2014; as applicable: Within 24 months after the 
effective date of this AD.
    (vi) For Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes and Model 
A340-211, -212, -213, -311, -312, and -313 airplanes; stringer 9 
junction between frame (FR) 10 and FR13; as specified in Airbus 
Service Bulletin A330-53-3235, Revision 01, dated January 14, 2015; 
or Airbus Service Bulletin A340-53-4225, Revision 01, dated January 
14, 2015; as applicable: Within 12 months after the effective date 
of this AD.
    (vii) For Model A340-200 and -300 Weight Variant (WV)00s 
airplanes; forward and rear fuselage; as specified in Airbus Service 
Bulletin A340-53-4224, dated December 15, 2014: Within 12 months 
after the effective date of this AD.
    (viii) For Model A340-200 and -300 WV00s airplanes; nose forward 
and center fuselage; as specified in Airbus Service Bulletin A340-
53-4224, dated December 15, 2014: Within 24 months after the 
effective date of this AD.
    (ix) For Model A330-200 and -300 pre-mod 49144 airplanes, and 
Model A340-200

[[Page 72518]]

and -300 WV20s airplanes; forward and rear fuselage, nose forward 
and center fuselage; as specified in Airbus Service Bulletin A330-
53-3234, dated December 8, 2014; or Airbus Service Bulletin A340-53-
4224, dated December 15, 2014; as applicable: Within 24 months after 
the effective date of this AD.
    (x) For Model A330-200 and -300 post-mod 49144 airplanes and 
Model A340-200 and -300 post-mod 49144 airplanes; nose forward and 
center fuselage; as specified in Airbus Service Bulletin A330-53-
3234, dated December 8, 2014; or Airbus Service Bulletin A340-53-
4224, dated December 15, 2014; as applicable: Within 24 months after 
the effective date of this AD.
    (2) Applicable areas (on both LH and RH sides) are identified in 
paragraphs (g)(2)(i) through (g)(2)(iv) of this AD.
    (i) Door cut-out corners of door surrounding panels (forward 
cargo door, mid PAX door, emergency exit door/PAX door 3, aft cargo 
door, bulk cargo door, aft PAX door), as specified in Airbus Service 
Bulletin A330-53-3232, dated November 4, 2014; or Airbus Service 
Bulletin A340-53-4222, dated November 25, 2014; as applicable.
    (ii) Forward PAX door surround panels, as specified in Airbus 
Service Bulletin A330-53-3233, dated September 26, 2014; or Airbus 
Service Bulletin A340-53-4223, dated September 26, 2014; as 
applicable.
    (iii) Fuselage skin doubler repairs, as specified in Airbus 
Service Bulletin A330-53-3234, dated December 8, 2014; or Airbus 
Service Bulletin A340-53-4224, dated December 15, 2014; as 
applicable.
    (iv) Stringer 9 junction between FR10 and FR13, as specified in 
Airbus Service Bulletin A330-53-3235, Revision 01, dated January 14, 
2015; or Airbus Service Bulletin A340-53-4225, Revision 01, dated 
January 14, 2015; as applicable.

(h) Corrective Actions

    If, during any review or inspection required by paragraph (g)(1) 
of this AD, it is determined that an SRM ADL was used on an area 
specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD to 
assess or control any structural damage, or any structural repair of 
an area specified in paragraphs (g)(2)(i) through (g)(2)(iv) of this 
AD was accomplished as specified in the instructions of the 
applicable SRM revision dated before April 2013 or SRM temporary 
revision (TR) dated before November 28, 2014: Within the applicable 
compliance time specified in paragraphs (g)(1)(i) through (g)(1)(x) 
of this AD, do the actions specified in paragraphs (h)(1) or (h)(2) 
of this AD, as applicable.
    (1) Revise the maintenance or inspection program, as applicable, 
with the applicable revised thresholds and intervals for the 
identified structural repairs embodied on the airplane, and 
accomplish all updated inspections, in accordance with the 
Accomplishment Instructions of the applicable service information 
identified in paragraphs (g)(2)(i) through (g)(2)(iv) of this AD, 
except as required by paragraphs (h)(1)(i) and (h)(1)(ii) of this 
AD.
    (i) Where the applicable service information identified in 
paragraphs (g)(2)(i) through (g)(2)(iv) of this AD specifies to 
contact Airbus for specific assessment, revise the maintenance or 
inspection program and accomplish all updated inspections, as 
applicable, using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA.
    (ii) Where the applicable service information identified in 
paragraphs (g)(2)(i) through (g)(2)(iv) of this AD specifies 
``current SRM,'' no SRM revision dated before April 2013 or SRM TR 
dated before November 28, 2014, is considered a ``current SRM.''
    (2) For any repair that was previously allowed in any revision 
of the Airbus A330 or A340 SRM, as applicable, dated before April 
2013; or in any SRM TR dated before November 28, 2014, to the 
applicable SRM, and is no longer allowed by the applicable SRM 
revision dated on or after April 2013: Make an assessment using a 
method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA 
DOA; and perform necessary corrective actions at the applicable 
times identified therein.

(i) Limitation on Repair/Replacement

    As of the effective date of this AD, for any structural damage 
in the areas identified in paragraphs (g)(2)(i) through (g)(2)(iv) 
of this AD that has exceeded the ADL, no repair or replacement may 
be done using an Airbus A330 or A340 SRM dated before April 2013, or 
any Airbus A330 or A340 SRM TR dated before November 28, 2014.

(j) 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: 9-ANM-116-AMOC-REQUESTS@faa.gov. 
Before using any approved AMOC, notify your appropriate principal 
inspector, or lacking a principal inspector, the manager of the 
local flight standards district office/certificate holding district 
office. The AMOC approval letter must specifically reference this 
AD.
    (2) Contacting the Manufacturer: For any requirement in this AD 
to obtain corrective actions from a manufacturer, the action must be 
accomplished using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA. If approved by the DOA, the approval must include 
the DOA-authorized signature.
    (3) Required for Compliance (RC): Except as required by 
paragraphs (h)(1)(i), (h)(1)(ii), and (h)(2) of this AD: If any 
service information contains procedures or tests that are identified 
as RC, those procedures and tests must be done to comply with this 
AD; any procedures or tests that are not identified as RC are 
recommended. Those procedures and tests that are not identified as 
RC may be deviated from using accepted methods in accordance with 
the operator's maintenance or inspection program without obtaining 
approval of an AMOC, provided the procedures and tests identified as 
RC can be done and the airplane can be put back in an airworthy 
condition. Any substitutions or changes to procedures or tests 
identified as RC require approval of an AMOC.

(k) Related Information

    Refer to Mandatory Continuing Airworthiness Information (MCAI) 
EASA AD 2015-0101R1, dated June 12, 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-
2016-0465.

(l) 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 A330-53-3232, dated November 4, 
2014.
    (ii) Airbus Service Bulletin A330-53-3233, dated September 26, 
2014.
    (iii) Airbus Service Bulletin A330-53-3234, dated December 8, 
2014.
    (iv) Airbus Service Bulletin A330-53-3235, Revision 01, dated 
January 14, 2015.
    (v) Airbus Service Bulletin A340-53-4222, dated November 25, 
2014.
    (vi) Airbus Service Bulletin A340-53-4223, dated September 26, 
2014.
    (vii) Airbus Service Bulletin A340-53-4224, dated December 15, 
2014.
    (viii) Airbus Service Bulletin A340-53-4225, Revision 01, dated 
January 14, 2015.
    (3) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone: +33 5 61 93 36 96; fax: +33 
5 61 93 44 51; email: account.airworth-eas@airbus.com; Internet: 
http://www.airbus.com.
    (4) You may view this service information at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue SW., Renton, WA. For 
information on the availability of this material at the FAA, call 
425-227-1221.
    (5) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

[[Page 72519]]

    Issued in Renton, Washington, on September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-24191 Filed 10-19-16; 8:45 am]
 BILLING CODE 4910-13-P
```