[Federal Register Volume 81, Number 229 (Tuesday, November 29, 2016)]
[Rules and Regulations]
[Pages 85837-85840]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-28335]



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  Federal Register / Vol. 81, No. 229 / Tuesday, November 29, 2016 / 
Rules and Regulations  

[[Page 85837]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5596; Directorate Identifier 2015-NM-121-AD; 
Amendment 39-18677; AD 2016-20-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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

SUMMARY: We are superseding Airworthiness Directive (AD) 2014-12-06 for 
certain Airbus Model A300 B4-600, B4-600R, and F4-600R series 
airplanes, and Model A300 C4-605R Variant F airplanes (collectively 
called Model A300-600 series airplanes); and Airbus Model A310 series 
airplanes. AD 2014-12-06 required repetitive ultrasonic or detailed 
inspections of the external area of the aft cargo door sill beam for 
cracking, and repair if necessary, and provided an optional one-time 
high frequency eddy current (HFEC) inspection that would terminate the 
repetitive inspections. This new AD requires the previously optional 
terminating HFEC inspection, and requires that it be done repetitively. 
This AD was prompted by findings of multiple fatigue cracks in the aft 
cargo door that indicated the need for additional, repetitive, HFEC 
inspections. We are issuing this AD to address the unsafe condition on 
these products.

DATES: This AD is effective January 3, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 3, 
2017.
    The Director of the Federal Register approved the incorporation by 
reference of a certain other publication listed in this AD as of July 
2, 2014 (79 FR 34403, June 17, 2014).

ADDRESSES: For service information identified in this final rule, 
contact Airbus SAS, Airworthiness Office--EAW, 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-
5596.

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-
5596, 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-2125; 
fax 425-227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to supersede AD 2014-12-06, Amendment 39-17867 (79 FR 34403, 
June 17, 2014) (``AD 2014-12-06''). AD 2014-12-06 applied to certain 
Airbus Model A300 B4-600, B4-600R, and F4-600R series airplanes, and 
Model A300 C4-605R Variant F airplanes (collectively called Model A300-
600 series airplanes); and Airbus Model A310 series airplanes. AD 2014-
12-06 required repetitive ultrasonic or detailed inspections of the 
external area of the aft cargo door sill beam for cracking, and repair 
if necessary. AD 2014-12-16 also provided an optional one-time HFEC 
inspection that would terminate the repetitive inspections. The NPRM 
published in the Federal Register on April 27, 2016 (81 FR 24745). The 
NPRM was prompted by findings of multiple fatigue cracks in the aft 
cargo door that indicated the need for repetitive HFEC inspections. The 
NPRM proposed to continue to require repetitive ultrasonic or detailed 
inspections of the external area of the aft cargo door sill beam for 
cracking, and repair if necessary. The NPRM also proposed to require 
the previously optional terminating HFEC inspection, and to require 
that it be done repetitively. We are issuing this AD to detect and 
correct fatigue cracking of the cargo door sill beam, lock fitting, and 
torsion box plate. Failure of one or more of these components could 
result in the loss of the door locking function and, subsequently, 
complete loss of the cargo door in flight with the risk of rapid 
decompression.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA 
Airworthiness Directive 2015-0150, dated July 23, 2015 (referred to 
after this as the Mandatory Continuing Airworthiness Information, or 
``the MCAI''), to correct an unsafe condition for certain Airbus Model 
A300 B4-600, B4-600R, and F4-600R series airplanes, and Model A300 C4-
605R Variant F airplanes (collectively called Model A300-600 series 
airplanes); and Airbus Model A310 series airplanes. The MCAI states:

    During accomplishment of Maintenance Review Board Report (MRBR) 
task 531625-01-1 on an A300-600 aeroplane having accumulated more 
than 25,000 flight cycles (FC) since aeroplane first flight, 
multiple fatigue cracks were found on the following parts:

--Aft cargo door sill beam Part Number (P/N) A53973085210.
--Lock fitting P/N A53978239002.
--Torsion box plate P/N A53973318206.

    Prompted by these findings, a stress analysis was performed 
during which it was discovered that there is no dedicated

[[Page 85838]]

scheduled maintenance task to inspect the affected area for fatigue 
damage.
    This condition, if not detected and corrected, could lead to 
failure of multiple lock fittings, possibly resulting in loss of the 
cargo door in flight and consequent explosive decompression of the 
aeroplane.
    To address this unsafe condition, Airbus issued Alert Operators 
Transmission (AOT) A53W005-14 providing instructions for inspection 
of the affected area.
    Consequently, EASA issued Emergency AD 2014-0097-E [which 
corresponded to FAA AD 2014-12-06] to require repetitive ultrasonic 
(US) inspections or detailed inspections (DET) of the aft cargo door 
sill beam external area, and/or a one-time High Frequency Eddy 
Current (HFEC) inspection of the aft cargo door sill beam internal 
structure and, depending on findings, accomplishment of corrective 
action(s).
    Since that [EASA] AD was issued, the results of further analysis 
have indicated that repetitive HFEC inspections need to be 
introduced.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2014-0097-E, which is superseded, and 
requires repetitive HFEC inspections of the concerned areas. The 
first HFEC inspection terminates the repetitive US/DET inspections.

    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-
5596.

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

    The Air Line Pilots Association, International stated that it 
supports the NPRM.

Request To Rewrite Reporting Requirements

    One commenter, Mark Hilborn, requested that we revise the structure 
of paragraph (i) of the proposed AD for clarity and to change the 
location where the reports should be sent. He stated that we could 
rewrite paragraph (i) of the proposed AD to remove the subparagraphs.
    We partially agree with the request. We have updated the contact 
information for submitting the reports. We do not find it necessary, 
however, to change the remainder of the paragraph since it is restated 
from AD 2014-12-06, and the compliance times are correct.

Request To Clarify the Terminating Actions

    Mark Hilborn requested we revise paragraph (m) of the proposed AD 
for clarity and to add new subparagraphs to aid in that.
    We agree with the request and have changed paragraph (m) of this AD 
accordingly.

Additional Changes Made in This Final Rule

    We have revised this AD to require the current version of the 
service information identified for the terminating action specified in 
this AD. This service information was revised to make a small tooling 
change; no additional work is necessary for airplanes on which the 
original version of this service information was accomplished. We have 
also added credit for airplanes on which the original version of this 
service information was accomplished, and made related changes 
accordingly.

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:
     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 the following service information, which 
describes procedures for repetitive HFEC inspections of the cargo door 
sill beam, lock fitting, and torsion box plate. These service bulletins 
are distinct since they apply to different airplane models.
     Airbus Service Bulletin A300-53-6179, dated December 12, 
2014.
     Airbus Service Bulletin A310-53-2139, dated December 12, 
2014.
    Airbus has also issued AOT A53W005-14, Revision 01, dated April 29, 
2014, which describes procedures for doing an ultrasonic inspection or 
detailed inspection of the aft cargo door sill beam external area for 
cracking.
    Additionally, Airbus has issued the following service information, 
which describes procedures for reinforcing the aft cargo door sill beam 
are between FR 60 and FR 63. These service bulletins are distinct since 
they apply to different airplane models.
     Airbus Service Bulletin A310-53-2141, Revision 01, dated 
July 2, 2015.
     Airbus Service Bulletin A300-53-6181, Revision 01, dated 
July 2, 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 75 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
----------------------------------------------------------------------------------------------------------------
Inspection.....................  12 work-hours x $85     N/A..............  $1,020 per         $76,500 per
                                  per hour = $1,020 per                      inspection cycle.  inspection
                                  inspection cycle.                                             cycle.
Reporting......................  1 work-hour x $85 per   N/A..............  $85..............  $6,375.
                                  hour = $85 per
                                  inspection cycle.
----------------------------------------------------------------------------------------------------------------

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800

[[Page 85839]]

Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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 AD 2014-12-06, Amendment 39-
17867 (79 FR 34403, June 17, 2014), and adding the following new AD:

2016-20-11 Airbus: Amendment 39-18677; Docket No. FAA-2016-5596; 
Directorate Identifier 2015-NM-121-AD.

(a) Effective Date

    This AD is effective January 3, 2017.

(b) Affected ADs

    This AD replaces AD 2014-12-06, Amendment 39-17867 (79 FR 34403, 
June 17, 2014) (``AD 2014-12-06'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), (c)(3), (c)(4), and (c)(5) of this AD, certificated 
in any category, all manufacturer serial numbers on which Airbus 
Modification 05438 has been embodied in production, except those on 
which Airbus Modification 12046 has been embodied in production.
    (1) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes.
    (2) Airbus Model A300 B4-605R and B4-622R airplanes.
    (3) Airbus Model A300 F4-605R and F4-622R airplanes.
    (4) Airbus Model A300 C4-605R Variant F airplanes.
    (5) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of fatigue cracks on the cargo 
door sill beam, lock fitting, and torsion box plate. We are issuing 
this AD to detect and correct fatigue cracking of the cargo door 
sill beam, lock fitting, and torsion box plate, which could result 
in the loss of the door locking function and subsequently, complete 
loss of the cargo door in flight with the risk of rapid 
decompression.

(f) Compliance

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

(g) Retained Inspection, With Revised Service Information

    This paragraph restates the requirements of paragraph (g)(1) of 
AD 2014-12-06, with revised service information. Within the 
compliance time identified in paragraph (g)(1), (g)(2), or (g)(3) of 
this AD, as applicable: Do an ultrasonic inspection or detailed 
inspection of the aft cargo door sill beam external area for 
cracking, in accordance with Airbus Alert Operators Transmission 
(AOT) A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, 
Revision 01, dated April 29, 2014. Repeat the inspection thereafter 
at intervals not to exceed 275 flight cycles. As of the effective 
date of this AD, only Airbus AOT A53W005-14, Revision 01, dated 
April 29, 2014, may be used to comply with the requirements of this 
paragraph.
    (1) For airplanes that have accumulated 30,000 flight cycles or 
more since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Within 50 flight cycles after July 
2, 2014.
    (2) For airplanes that have accumulated 18,000 flight cycles or 
more, but fewer than 30,000 flight cycles since the airplane's first 
flight as of July 2, 2014 (the effective date of AD 2014-12-06): 
Within 275 flight cycles after July 2, 2014.
    (3) For airplanes that have accumulated fewer than 18,000 flight 
cycles since the airplane's first flight as of July 2, 2014 (the 
effective date of AD 2014-12-06): Before exceeding 18,275 flight 
cycles since the airplane's first flight.

(h) Retained Optional Terminating Action, With Revised Service 
Information and Specific Delegation Approval Language

    This paragraph restates the provisions of paragraph (h) of AD 
2014-12-06, with revised service information and specific delegation 
approval language. Accomplishment of a high frequency eddy current 
(HFEC) inspection for cracking, in accordance with Airbus AOT 
A53W005-14, dated April 22, 2014; or Airbus AOT A53W005-14, Revision 
01, dated April 29, 2014; terminates the repetitive inspections 
required by paragraph (g) of this AD for that airplane. If any 
cracking is found during the HFEC inspection, before further flight, 
repair 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).

(i) Retained Reporting Requirement, With Revised Contact Information

    This paragraph restates the provisions of paragraph (i) of AD 
2014-12-06, with revised contact information. Submit a report of the 
findings (both positive and negative) of the inspection required by 
paragraph (g) of this AD to ``Airbus Service Bulletin Reporting 
Online Application'' on Airbus World (https://w3.airbus.com/), at 
the applicable time specified in paragraph (i)(1) or (i)(2) of this 
AD. The report must include the inspection results, including no 
findings.
    (1) If the inspection was done on or after the effective date of 
this AD: Submit the report within 30 days after the inspection.
    (2) If the inspection was done before the effective date of this 
AD: Submit the report within 30 days after the effective date of 
this AD.

(j) Definition of Airplane Groups

    Paragraphs (k)(1), (k)(2), and (k)(3) of this AD refer to 
airplane groups, as identified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD.
    (1) Airplanes on which an HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14.
    (2) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, and that have accumulated more 
than 18,000 total flight cycles as of the effective date of this AD.

[[Page 85840]]

    (3) Airplanes on which no HFEC inspection was accomplished as 
specified in Airbus AOT A53W005-14, that have accumulated 18,000 
total flight cycles or fewer as of the effective date of this AD.

(k) New Repetitive HFEC Inspections and Repair

    At the applicable time specified in paragraph (k)(1), (k)(2), or 
(k)(3) of this AD: Do an HFEC inspection for fatigue cracking of the 
cargo door sill beam, lock fitting, and torsion box plate, in 
accordance with Airbus Service Bulletin A300-53-6179, dated December 
12, 2014; or Airbus Service Bulletin A310-53-2139, dated December 
12, 2014; as applicable. Repeat the HFEC inspection thereafter at 
intervals not to exceed 4,600 flight cycles.
    (1) For airplanes identified in paragraph (j)(1) of this AD: 
Inspect within 4,600 flight cycles after the most recent HFEC 
inspection specified in Airbus AOT A53W005-14.
    (2) For airplanes identified in paragraph (j)(2) of this AD: 
Inspect within 2,000 flight cycles after the effective date of this 
AD.
    (3) For airplanes identified in paragraph (j)(3) of this AD: 
Inspect before exceeding 13,000 total flight cycles since the 
airplane's first flight, or within 2,000 flight cycles after the 
effective date of this AD, whichever occurs later.

(l) Corrective Action

    If any crack is found during any inspection required by 
paragraph (g) or (k) of this AD: Before further flight, repair using 
a method approved by the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA; or the EASA; or Airbus's EASA 
DOA.

(m) Terminating Action for Repetitive Inspections

    This paragraph identifies the requirements to terminate 
repetitive inspections mandated by this AD.
    (1) For any airplane identified in paragraphs (j)(2) and (j)(3) 
of this AD, accomplishment of the initial inspection required by 
paragraph (k) of this AD terminates the repetitive inspections 
required by paragraph (g) of this AD.
    (2) For any airplane identified in paragraphs (c)(1) through 
(c)(5) of this AD, accomplishment of Airbus Service Bulletin A310-
53-2141, Revision 01, dated July 2, 2015; or Airbus Service Bulletin 
A300-53-6181, Revision 01, dated July 2, 2015; as applicable; 
terminates the repetitive inspections required by paragraph (k) of 
this AD.

(n) Credit for Previous Actions

    This paragraph provides credit for actions provided in paragraph 
(m)(2) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A300-53-
6181, dated June 26, 2015; or Airbus Service Bulletin A310-53-2141, 
dated June 26, 2015; as applicable.

(o) 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: Dan Rodina, 
Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-2125; fax 425-227-1149. Information may be 
emailed to: [email protected]. 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: 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) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.
    (4) Required for Compliance (RC): Except as required by 
paragraph (l) 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.

(p) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA Airworthiness Directive 2015-0150, dated July 23, 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-2016-5596.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (q)(5) and (q)(6) of this AD.

(q) 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 
January 3, 2017.
    (i) Airbus Alert Operators Transmission (AOT) A53W005-14, 
Revision 01, dated April 29, 2014.
    (ii) Airbus Service Bulletin A310-53-2141, Revision 01, dated 
July 2, 2015.
    (iii) Airbus Service Bulletin A300-53-6179, dated December 12, 
2014.
    (iv) Airbus Service Bulletin A300-53-6181, Revision 01, dated 
July 2, 2015.
    (v) Airbus Service Bulletin A310-53-2139, dated December 12, 
2014.
    (4) The following service information was approved for IBR on 
July 2, 2014 (79 FR 34403, June 17, 2014).
    (i) Airbus AOT A53W005-14, dated April 22, 2014.
    (ii) Reserved.
    (5) For service information identified in this AD, contact 
Airbus SAS, Airworthiness Office--EAW, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; email [email protected]; 
Internet http://www.airbus.com. You may view this service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.
    (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: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on September 28, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2016-28335 Filed 11-28-16; 8:45 am]
 BILLING CODE 4910-13-P