Airworthiness Directives; Airbus Airplanes

[Federal Register Volume 82, Number 27 (Friday, February 10, 2017)]
[Rules and Regulations]
[Pages 10255-10258]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-01776]



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Federal Register / Vol. 82, No. 27 / Friday, February 10, 2017 / 
Rules and Regulations

[[Page 10255]]



DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2016-5040; Directorate Identifier 2013-NM-192-AD; 
Amendment 39-18787; AD 2017-02-08]
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 A300 series airplanes; and 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). This AD was 
prompted by a determination that certain inspection thresholds and 
intervals must be reduced. This AD requires repetitive detailed 
inspections for corrosion of the lower wing root joint, and related 
investigative and corrective actions if necessary. We are issuing this 
AD to address the unsafe condition on these products.

DATES: This AD is effective March 17, 2017.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of March 17, 
2017.

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-
5040.

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-
5040; 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: 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 by adding an AD that would apply to certain Airbus Model A300 
series airplanes; and 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). The NPRM published in the 
Federal Register on April 5, 2016 (81 FR 19509) (``the NPRM'').
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2013-0230, dated September 24, 2013 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for certain Airbus Model A300 series 
airplanes; and 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). The MCAI states:

    Several cases of corrosion on the lower wing root joint, located 
in the wing bottom skin inboard and outboard of the external lower 
surface splice, have been reported by operators.
    This condition, if not detected and corrected, could affect the 
structural integrity of the airframe.
    Prompted by these findings, [Direction G[eacute]n[eacute]rale de 
l'Aviation Civile] (DGAC) France issued AD 1997-006-210 [which 
corresponds to FAA AD 98-21-34, Amendment 39-10842 (63 FR 55524, 
October 16, 1998)] to require repetitive inspections to detect the 
presence of corrosion and prevent crack propagation at the wing 
bottom skin, inboard and outboard of the Rib 1 external lower 
surface splice, between Frame (FR) 40 and FR47.
    DGAC France * * * issued [an AD] to expand the choice of 
applicable Service Bulletins (SB). [The] DGAC France AD * * * was 
issued to allow A300-600 operators to use Revision 04 of Airbus SB 
A300-57-6047, converting flight cycles/''Fatigue rating'' into 
flight cycles (FC)/flight hours (FH).
    Subsequently, Airbus modification 10599 was developed to improve 
the corrosion behaviour of the area. This improvement allowed 
refining the inspection programme of the A300-600 aeroplane. For 
post-modification 10599 A300-600 aeroplanes, the application of the 
Maintenance Review Board Report (MRBR) inspection tasks was deemed 
sufficient for maintaining an adequate level of safety on these 
aeroplanes.
    Consequently, EASA issued AD 2008-0208 (later revised), 
retaining the requirements of [a] DGAC France AD * * *, which was 
superseded, to require the use of Airbus SB A300-57-6047 Revision 05 
for the inspections and to exclude post-modification 10599 A300-600 
aeroplanes from the Applicability.
    Since EASA AD 2008-0208R1 was issued, a fleet survey and updated 
Fatigue and Damage Tolerance analyses have been performed in order 
to substantiate the second A300-600 Extended Service Goal (ESG2) 
exercise. The results of these analyses determined that the 
threshold and interval must be reduced to allow timely detection of 
these cracks and the accomplishment of an applicable corrective 
action.
    For the reasons described above, this [EASA] AD takes over and 
retains the requirements for A300 and A300-600 aeroplanes from EASA 
AD 2008-0208R1 (which has been revised, remaining applicable only to 
A310 aeroplanes) and requires accomplishment of the inspections 
within the new thresholds and intervals.

    Required actions include repetitive detailed inspections for 
corrosion of the

[[Page 10256]]

rib 1 external lower surface splice between FR40 and FR47, repetitive 
fatigue inspections for cracking of the fasteners and on the surface of 
the forward and aft lower surface panels if necessary, and corrective 
actions (including application of new protective coating, removal of 
corrosion, and measurement of the reworked depth) if necessary.
    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-
5040.

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.

Request To Clarify the Applicability

    United Parcel Service (UPS) requested that we change the 
information in paragraph (c), Applicability, of the proposed AD. UPS 
explained that paragraph (c) of the proposed AD defines the airplane 
models applicable to the proposed rule, then has an exclusion later in 
paragraph (g) of the proposed AD. UPS reasoned that we should simplify 
by having related information in the same location, and suggested we 
combine paragraph (c) and paragraph (g) of the proposed AD into a 
single paragraph (c) of the proposed AD.
    For the reasons stated by the commenter, we agree to include the 
phrase, ``except those on which Airbus modification 10599 has been 
incorporated,'' in paragraph (c)(2) of this AD. However, we disagree 
with moving the statement, ``As of the effective date of this AD, the 
actions specified in AD 98-21-34, Amendment 39-10842 (63 FR 55524, 
October 16, 1998) (``AD 98-21-34'') are no longer required'' from 
paragraph (g) of this AD to paragraph (c) of this AD because the 
Applicability should not include this type of information; it is 
appropriately included in other regulatory text such as paragraph (g) 
of this AD.

Request To Clarify the Headings of Paragraphs (h) and (i) of the 
Proposed AD

    UPS requested that we revise the headings of paragraphs (h) and (i) 
of the proposed AD because the paragraph titles do not reflect what is 
contained within the respective paragraphs. UPS explained that 
paragraph (h) of the proposed AD does not contain any corrective 
actions, and paragraph (i) of the proposed AD contains fatigue 
inspection requirements.
    For the reasons stated by the commenter, we agree and have revised 
the headings of both paragraphs (h) and (i) of this AD.

Request for Grace Period

    UPS stated that upon its review of the fatigue inspection 
requirements, it identified that there is not a transition/grace period 
for airplanes on which inspections are already being accomplished, but 
for which the new repetitive inspection intervals have already been 
exceeded due to the service bulletin interval reductions.
    We agree with the commenter's statement. We had erroneously 
specified Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011, in the compliance time in paragraph (i)(2)(ii)(B) of 
the proposed AD; the correct reference is Airbus Service Bulletin A300-
57-6047, Revision 05, dated May 27, 2008. We have changed paragraph 
(i)(2)(ii)(B) of this AD to include a grace period of 500 flight cycles 
or 1,050 flight hours (whichever occurs first), without exceeding the 
compliance time specified in Airbus Service Bulletin A300-57-6047, 
Revision 05, dated May 27, 2008.

Request To Remove Paragraph (j) of the Proposed AD

    UPS requested that we delete paragraph (j) of the proposed AD. UPS 
explained that paragraphs (j)(1) and (j)(2) of the proposed AD identify 
differences between the service bulletin requirements specified by the 
original equipment manufacturer (OEM) and the proposed AD. UPS stated 
that in its review of paragraphs (j)(1) and (j)(2) of the proposed AD, 
it does not recognize a difference between contacting Airbus for 
corrective action, and using a method approved by the FAA for either 
situation. UPS reasoned that, as the discrepancy is located on primary 
structure and allowable/approved rework limits are exceeded, damage 
tolerance analysis is required as part of the repair definition 
process. UPS adds that the existing OEM process, the Repair Design 
Approval Sheet (RDAS), contains instructions for continued 
airworthiness and is approved by an EASA-designated airworthiness 
engineer. Based on the existing process and procedures in place, UPS 
does not believe that paragraph (j) of the proposed AD is necessary.
    We disagree with the request to delete paragraph (j) of this AD. 
Paragraph (j)(1) of this AD is required to address certain inspection 
findings. The service information specifies that Airbus be contacted 
for corrective action; however, paragraph (j)(1) of this AD requires 
that one of the specific organizations identified must approve those 
corrective actions. Likewise, paragraph (j)(2) of this AD specifies the 
appropriate organizations for compliance time determinations. 
Therefore, we have not changed this AD in this regard.

Request To Define Average Flight Time (AFT)

    UPS requested that we revise paragraph (k) of the proposed AD to 
match paragraph (i) of AD 2016-07-20, Amendment 39-18465 (81 FR 21255, 
April 11, 2016). UPS reasoned that AD 2016-07-20 clearly defines when 
the AFT value is calculated in subsequent repetitive inspection 
interval determinations. UPS explained that recent FAA ADs have 
included using AFT to determine repetitive inspection intervals, but 
the definition of calculating the AFT value has varied among ADs, which 
further complicates compliance across several mandatory ADs.
    For the reasons stated by the commenter, we have added more 
specific criteria for establishing the AFT in paragraph (k) of this AD.

Request To Include Approval for Previous Alternative Methods of 
Compliance (AMOCs)

    UPS requested that we revise paragraph (m) of the proposed AD to 
include approval for previous AMOCs. UPS explained that other final 
rules include approved AMOCs for prior or superseded ADs. UPS explained 
further that it received AMOC approval for AD 98-21-34 in which the 
intent is embodied within the proposed AD (i.e., no additional action 
for an airplane with modification 10599 embodied), and that there may 
be other AMOC approvals applicable to the previous AD.
    We agree for the reasons stated by the commenter. We added the 
previous AMOC approval information in paragraph (m)(1)(ii) of this 
final rule.

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:
    <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.

[[Page 10257]]

    We also determined that these changes will not increase the 
economic burden on any operator or increase the scope of this AD.

Related Service Information Under 1 CFR Part 51

    We reviewed Airbus Service Bulletin A300-57-0204, Revision 01, 
dated April 2, 1999; and Airbus Service Bulletin A300-57-6047, Revision 
06, dated October 17, 2011. This service information describes 
procedures for repetitive detailed inspections for corrosion of the rib 
1 external lower surface splice between FR40 and FR47, repetitive 
fatigue inspections for cracking of the fasteners and on the surface of 
the forward and aft lower surface panels if necessary, and corrective 
actions (including application of new protective coating, removal of 
corrosion, and measurement of the reworked depth) if necessary. These 
documents are distinct since they apply to different airplane models. 
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 29 airplanes of U.S. registry. We 
also estimate that it would take about 8 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 $19,720, or $680 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 8 work-hours, for a cost of $680 per product. We have no way 
of determining the number of aircraft that might need these actions.

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):

2017-02-08 Airbus: Amendment 39-18787; Docket No. FAA-2016-5040; 
Directorate Identifier 2013-NM-192-AD.

(a) Effective Date

    This AD is effective March 17, 2017.

(b) Affected ADs

    This AD affects AD 98-21-34, Amendment 39-10842 (63 FR 55524, 
October 16, 1998) (``AD 98-21-34'').

(c) Applicability

    This AD applies to Airbus airplanes, certificated in any 
category, identified in paragraphs (c)(1) and (c)(2) of this AD.
    (1) All Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-103, 
and B4-203 airplanes.
    (2) Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes, except those on 
which Airbus modification 10599 has been incorporated.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by reports of corrosion on the lower wing 
root joint located in the wing bottom skin inboard and outboard of 
the external lower surface splice, and the determination that 
certain existing inspection thresholds and intervals must be 
reduced. We are issuing this AD to detect and correct corrosion and 
cracking on the lower wing root joint, which could reduce the 
structural integrity of the airframe.

(f) Compliance

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

(g) Airplanes Excluded From the Requirements of AD 98-21-34 and This AD

    For Model A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, 
F4-605R, F4-622R, and C4-605R Variant F airplanes, on which Airbus 
modification 10599 has been incorporated: As of the effective date 
of this AD, the actions specified in AD 98-21-34 are no longer 
required. No action is required by this AD.

(h) Repetitive Inspections

    Within 60 months since the airplane's first flight, or within 60 
months since accomplishment of the last inspection specified in 
Airbus Service Bulletin A300-57-0204 or A300-57-6047, whichever 
occurs later: Do a detailed inspection for corrosion of the rib 1 
external lower surface splice between frame (FR)40 and FR47, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable. Repeat the inspection thereafter at intervals not to 
exceed 60 months. Accomplishment of the initial inspection required 
by this paragraph terminates the requirements of AD 98-21-34 for 
Model A300 and A300-600 series airplanes.

(i) Corrective Actions, Repetitive Fatigue Inspections, and Repair

    If any corrosion is found during any inspection required by 
paragraph (h) of this AD, do the actions specified in paragraph 
(i)(1) and (i)(2) of this AD.
    (1) Before further flight, do all applicable corrective actions, 
in accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A300-57-0204, Revision 01, dated April 2, 1999; or Airbus 
Service Bulletin A300-57-6047, Revision 06, dated October 17, 2011; 
as applicable; except as required by paragraph (j)(1) of this AD.
    (2) At the applicable time specified in paragraph (i)(2)(i) or 
(i)(2)(ii) of this AD, except as required by paragraph (j)(2) of 
this AD: Do fatigue inspections to detect cracks of

[[Page 10258]]

the fasteners and on the surface of the forward and aft lower 
surface panels, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 
1999; or Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011; as applicable. Repeat the fatigue inspections 
thereafter at the applicable interval specified in paragraph B.(5) 
of Airbus Service Bulletin A300-57-0204, Revision 01, dated April 2, 
1999; or Figure A-FBGAA, Sheet 01, of Airbus Service Bulletin A300-
57-6047, Revision 06, dated October 17, 2011; as applicable; except 
as required by paragraph (j)(2) of this AD. If any cracking is found 
during any fatigue inspection required by this paragraph: 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) For Model A300 series airplanes: Do the initial inspection 
at the applicable time specified in paragraph B.(5) of Airbus 
Service Bulletin A300-57-0204, Revision 01, dated April 2, 1999.
    (ii) For Model A300-600 series airplanes: Do the initial 
inspection at the later of the times specified in paragraphs 
(i)(2)(ii)(A) and (i)(2)(ii)(B) of this AD.
    (A) At the applicable time specified in Figure A-FBGAA, Sheet 
01, of Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011.
    (B) Within 500 flight cycles or 1,050 flight hours after the 
effective date of this AD, whichever occurs first, without exceeding 
the compliance time specified in Airbus Service Bulletin A300-57-
6047, Revision 05, dated May 27, 2008.

(j) Exceptions to Service Bulletin Specifications

    (1) Where Airbus Service Bulletin A300-57-0204, Revision 01, 
dated April 2, 1999; or Airbus Service Bulletin A300-57-6047, 
Revision 06, dated October 17, 2011; specifies to contact Airbus for 
appropriate corrective action, this AD requires repair before 
further flight using a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or 
Airbus's EASA DOA.
    (2) Where Airbus Service Bulletin A300-57-6047, Revision 06, 
dated October 17, 2011, specifies to contact Airbus for the 
appropriate threshold or repetitive interval, this AD requires that 
the compliance time be determined using a method approved by the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA; or Airbus's EASA DOA.

(k) Calculating Average Flight Time (AFT)

    For the purposes of paragraph (i)(2) of this AD, the AFT must be 
established as specified in paragraphs (k)(1), (k)(2), and (k)(3) of 
this AD.
    (1) For the initial inspection, the AFT is the total accumulated 
flight hours, counted from take-off to touch-down, divided by the 
total accumulated flight cycles at the effective date of this AD.
    (2) For the first repeated inspection interval, the AFT is the 
total accumulated flight hours divided by the total accumulated 
flight cycles at the time of the inspection threshold.
    (3) For all inspection intervals onward, the AFT is the flight 
hours accumulated between the two most recent inspections divided by 
the flight cycles accumulated between the two most recent 
inspections.

(l) Credit for Previous Actions

    This paragraph provides credit for the inspections and 
corrective actions required by paragraphs (h) and (i) 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) through (l)(3) of this AD.
    (1) Airbus Service Bulletin A300-57-6047, Revision 02, dated 
April 2, 1999.
    (2) Airbus Service Bulletin A300-57-6047, Revision 03, dated 
September 28, 1999.
    (3) Airbus Service Bulletin A300-57-6047, Revision 05, dated May 
27, 2008.

(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 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].
    (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 98-21-34 are approved as 
AMOCs for the corresponding provisions of paragraphs (h) and (i) of 
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.

(n) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2013-0230, dated September 24, 2013, 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-2016-5040.
    (2) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (o)(3) and (o)(4) 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.
    (i) Airbus Service Bulletin A300-57-0204, Revision 01, dated 
April 2, 1999.
    (ii) Airbus Service Bulletin A300-57-6047, Revision 06, dated 
October 17, 2011.
    (3) 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.
    (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.

    Issued in Renton, Washington, on January 18, 2017.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2017-01776 Filed 2-9-17; 8:45 am]
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