AD 2017-25-09

[Federal Register Volume 82, Number 239 (Thursday, December 14, 2017)]
[Rules and Regulations]
[Pages 58715-58718]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2017-26627]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2017-0714; Product Identifier 2017-NM-042-AD; Amendment 
39-19123; AD 2017-25-09]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2012-21-04, 
which applied to all Airbus Model A300 series airplanes; Model A310 
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).
    AD 2012-21-04 required repetitive inspections for, and replacement 
of, any cracked hood halves of fuel pump canisters. Since we issued AD 
2012-21-04, we allowed inspections of the wing-outer tank and trim tank 
fuel pump canister hood halves to be terminated.
    This new AD retains the requirements of AD 2012-21-04, reinstates 
the terminated inspections, and adds optional terminating actions. This 
AD was prompted by reports of cracked fuel pump canister hoods located 
in fuel tanks and new in-service events of wing-outer tank fuel pump 
canister hood cracking. We are issuing this AD to address the unsafe 
condition on these products.

DATES: This AD is effective January 18, 2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 18, 
2018.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
November 27, 2012 (77 FR 64701, October 23, 2012).

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: <a href="/cdn-cgi/l/email-protection#1e7f7d7d716b706a307f776c69716c6a76337b7f6d5e7f776c7c6b6d307d7173"><span class="__cf_email__" data-cfemail="b7d6d4d4d8c2d9c399d6dec5c0d8c5c3df9ad2d6c4f7d6dec5d5c2c499d4d8da">[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 Standards Branch, 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-2017-0714.

Examining the AD Docket

    You may examine the AD docket on the internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> by searching for and locating Docket No. FAA-2017-
0714; 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 Section, Transport Standards Branch, 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 2012-21-04, Amendment 39-17220 (77 FR 64701, 
October 23, 2012) (``AD 2012-21-04''). AD 2012-21-04 applied to all 
Airbus Model A300 series airplanes; Model A310 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 August 2, 2017 (82 FR 
35911). The NPRM was prompted by reports of cracked fuel pump canister 
hoods located in fuel tanks and new in-service events of wing-outer 
tank fuel pump canister hood cracking. The NPRM proposed to retain the 
requirements of AD 2012-21-04, reinstate terminated inspections, and 
add optional terminating actions. We

[[Page 58716]]

are issuing this AD to prevent any detached canister hood fragments/
debris from being ingested into the fuel feed system, and becoming a 
potential source of ignition with consequent fire or explosion.
    The European Aviation Safety Agency (EASA), which is the Technical 
Agent for the Member States of the European Union, has issued EASA AD 
2017-0051, dated March 23, 2017 (referred to after this as the 
Mandatory Continuing Airworthiness Information, or ``the MCAI''), to 
correct an unsafe condition for all Airbus Model A300 series airplanes; 
Model A310 series airplanes; and Model A300-600 series airplanes. The 
MCAI states:

    Reports were received of finding cracked fuel pump canister 
hoods located in fuel tanks on in-service aeroplanes. Initial 
analyses, laboratory testing and examinations suggested that 
vibration-induced fatigue could have caused these cracks. However, 
initial data could not exclude some other potential contributing 
factors.
    This condition, if not detected and corrected, could lead to 
detached canister hood fragments or debris being ingested into the 
fuel feed system. In addition, metallic debris inside the fuel tank 
could result in a potential source of fuel vapour ignition, possibly 
resulting in a fire or fuel tank explosion and consequent loss of 
the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2011-
0124 (later revised) [FAA AD 2012-21-04 corresponds to EASA AD 2011-
0124] to require repetitive inspections of the canister hood halves 
installed on all fuel pump canisters and, if any damage was found, 
replacement. EASA AD 2011-0124R1 introduced an optional terminating 
action for the wing inner and centre fuel tanks, and cancelled the 
repetitive inspections of the fuel pump canister hoods in outer wing 
and trim tanks, for which no cracks had been reported following the 
initial inspection.
    Since that [EASA] AD was issued, new in service events of outer 
tank fuel pump canister hood cracking have been reported. 
Consequently, the canister hoods of the outer tank fuel pumps and 
trim tank fuel pumps will need to be inspected.
    For the reasons described above, this [EASA] AD retains the 
requirements of EASA AD 2011-0124R1, which is superseded, retaining 
the repetitive inspections of fuel pump canister hoods in wing inner 
and centre tanks, and reintroduces repetitive detailed inspections 
(DET) for outer tank and trim tank fuel pump canister hoods. This 
[EASA] AD also retains the existing optional terminating action for 
the repetitive DET of wing inner and centre tank fuel pump canister 
hoods, and introduces a new optional terminating action for the 
repetitive DET of the outer and trim tank fuel pump canister hoods 
required by this [EASA] AD.

    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-2017-
0714.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received. The commenter, John 
Sanderson, supported the NPRM.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD as proposed except for 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> Airbus Service Bulletin A300-28-0089, Revision 03, dated 
December 16, 2016. This service information describes procedures for 
repetitive detailed inspections of all fuel pump locations (center, 
wing-inner, and wing-outer tank), and replacing any cracked hood halves 
of fuel pump canisters.
    <bullet> Airbus Service Bulletin A300-28-0092, Revision 01, dated 
August 29, 2014; Airbus Service Bulletin A300-28-6110, Revision 01, 
dated August 29, 2014; and Airbus Service Bulletin A310-28-2175, 
Revision 01, dated August 29, 2014. This service information describes 
procedures for replacement of the hood halves of the fuel pump 
canisters with newer design hood halves for the wing-inner tank and the 
center tank fuel pumps. These documents are distinct since they apply 
to different airplane models.
    <bullet> Airbus Service Bulletin A300-28-0094, Revision 00, dated 
January 9, 2017. This service information describes procedures for 
replacement of the hood halves of the fuel pump canisters with newer 
design hood halves for the wing-outer tank.
    <bullet> Airbus Service Bulletin A300-28-6106, Revision 03, dated 
December 16, 2016; and Airbus Service Bulletin A310-28-2173, Revision 
03, dated December 16, 2016. This service information describes 
procedures for repetitive detailed inspections of all fuel pump 
locations (center, wing-inner, wing-outer, and trim tank), and 
replacing any cracked hood halves of fuel pump canisters. These 
documents are distinct since they apply to different airplane models.
    <bullet> Airbus Service Bulletin A300-28-6114, Revision 00, dated 
January 9, 2017; and Airbus Service Bulletin A310-28-2178, Revision 00, 
dated January 9, 2017. This service information describes procedures 
for replacement of the hood halves of the fuel pump canisters with 
newer design hood halves for the wing-outer tank and the trim tank fuel 
pumps. 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 168 airplanes of U.S. registry.
    The actions required by AD 2012-21-04, and retained in this AD take 
about 12 work-hours per product, at an average labor rate of $85 per 
workhour. Based on these figures, the estimated cost of the actions 
that are required by AD 2012-21-04 is $1,020 per product.
    We also estimate that it will take about 9 work-hours per product 
to comply with the new basic requirements of this AD, at an average 
labor rate of $85 per work-hour. Based on these figures, we estimate 
the cost of the new basic requirements of this AD on U.S. operators to 
be $128,520, or $765 per product.
    In addition, we estimate that the optional terminating actions will 
take about 1 work-hour and require parts costing $255, for a cost of 
$340 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

[[Page 58717]]

products identified in this rulemaking action.
    This AD is issued in accordance with authority delegated by the 
Executive Director, Aircraft Certification Service, as authorized by 
FAA Order 8000.51C. In accordance with that order, issuance of ADs is 
normally a function of the Compliance and Airworthiness Division, but 
during this transition period, the Executive Director has delegated the 
authority to issue ADs applicable to transport category airplanes to 
the Director of the System Oversight Division.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD will not have a substantial direct 
effect on the States, on the relationship between the national 
government and the States, or on the distribution of power and 
responsibilities among the various levels of government.
    For the reasons discussed above, I certify that this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979);
    3. Will not affect intrastate aviation in Alaska; and
    4. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing Airworthiness Directive (AD) 
2012-21-04, Amendment 39-17220 (77 FR 64701, October 23, 2012), and 
adding the following new AD:

2017-25-09 Airbus: Amendment 39-19123; Docket No. FAA-2017-0714; 
Product Identifier 2017-NM-042-AD.

(a) Effective Date

    This AD is effective January 18, 2018.

(b) Affected ADs

    This AD replaces AD 2012-21-04, Amendment 39-17220 (77 FR 64701, 
October 23, 2012) (``AD 2012-21-04'').

(c) Applicability

    This AD applies to the airplanes identified in paragraphs 
(c)(1), (c)(2), and (c)(3) of this AD, certificated in any category, 
all certificated models, all manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, B2-203, B4-2C, B4-
103, and B4-203 airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.
    (3) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes, Model A300 B4-605R and B4-622R airplanes, Model A300 F4-
605R and F4-622R airplanes, and Model A300 C4-605R Variant F 
airplanes.

(d) Subject

    Air Transport Association (ATA) of America Code 28, Fuel.

(e) Reason

    This AD was prompted by reports of cracked fuel pump canister 
hoods located in fuel tanks and new in-service events of wing-outer 
tank fuel pump canister hood cracking. We are issuing this AD to 
prevent any detached canister hood fragments/debris from being 
ingested into the fuel feed system, and becoming a potential source 
of ignition with consequent fire or explosion.

(f) Compliance

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

(g) Retained Initial Inspection and Replacement, With Revised 
Requirements and Service Information

    This paragraph restates the requirements of paragraph (g) of AD 
2012-21-04, with revised requirements and service information. 
Within 30 months after November 27, 2012 (the effective date of AD 
2012-21-04), do a detailed inspection for cracking of the fuel pump 
canister hood halves installed on all center and wing-inner tank 
fuel pump canisters having part numbers (P/N) 2052C11, 2052C12, and 
C93R51-601, in accordance with the Accomplishment Instructions of 
the service bulletin specified in paragraph (g)(1), (g)(2), or 
(g)(3) of this AD, as applicable. If any crack is found on any fuel 
pump canister hood half during any inspection, before further 
flight, replace the fuel pump canister hood half, in accordance with 
the Accomplishment Instructions of the service bulletin specified in 
paragraph (g)(1), (g)(2), or (g)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Mandatory Service 
Bulletin A300-28-0089, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A300-28-
0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Mandatory 
Service Bulletin A300-28-6106, Revision 01, including Inspection 
Findings--Reporting Sheet, dated April 15, 2011; or Airbus Service 
Bulletin A300-28-6106, Revision 03, dated December 16, 2016. As of 
the effective date of this AD, only use Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Mandatory Service 
Bulletin A310-28-2173, Revision 01, including Inspection Findings--
Reporting Sheet, dated April 15, 2011; or Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016. As of the 
effective date of this AD, only use Airbus Service Bulletin A310-28-
2173, Revision 03, dated December 16, 2016.

(h) Retained Repetitive Inspections, With No Changes

    This paragraph restates the requirements of paragraph (h) of AD 
2012-21-04, with no changes. Within 30 months after accomplishing 
the actions specified in paragraph (g) of this AD, and thereafter at 
intervals not to exceed 30 months, repeat the detailed inspection 
specified in paragraph (g) of this AD.

(i) New Repetitive Inspections and Replacement of the Wing-Outer Tank 
and Trim Tank Fuel Pump Canister Hood Halves

    Within 30 months after the effective date of this AD, do a 
detailed inspection for cracking of the wing-outer tank and trim 
tank, as applicable, fuel pump canister hood halves installed on all 
fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-601, in 
accordance with the Accomplishment Instructions of the service 
bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of this 
AD, as applicable. Repeat the inspection thereafter at intervals not 
to exceed 30 months. If any crack is found on any fuel pump canister 
hood half during any inspection, before further flight, replace the 
fuel pump canister hood half, in accordance with the Accomplishment 
Instructions of the service bulletin specified in paragraph (i)(1), 
(i)(2), or (i)(3) of this AD, as applicable.
    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0089, Revision 03, dated December 16, 2016.
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6106, Revision 03, dated December 16, 2016.
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2173, Revision 03, dated December 16, 2016.

(j) New Optional Terminating Actions

    Replacement of the fuel pump canister hood halves installed on 
all fuel pump canisters having P/Ns 2052C11, 2052C12, and C93R51-
601, constitutes terminating action for the inspections required by 
paragraphs (g) and (h) of this AD for that airplane. The replacement 
of the fuel pump canister hood halves must be done in accordance 
with the Accomplishment Instructions of the service information 
specified in paragraph (j)(1), (j)(2), or (j)(3) of this AD, as 
applicable.

[[Page 58718]]

    (1) For Model A300 series airplanes: Airbus Service Bulletin 
A300-28-0092, Revision 01, dated August 29, 2014 (for center and 
wing-inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-0094, Revision 00, dated January 9, 2017 (for wing-
outer tank fuel pump canister hood halves).
    (2) For Model A300-600 series airplanes: Airbus Service Bulletin 
A300-28-6110, Revision 01, dated August 29, 2014 (for center and 
wing-inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A300-28-6114, Revision 00, dated January 9, 2017 (for wing-
outer tank and trim tank fuel pump canister hood halves).
    (3) For Model A310 series airplanes: Airbus Service Bulletin 
A310-28-2175, Revision 01, dated August 29, 2014 (for center and 
wing-inner tank fuel pump canister hood halves); and Airbus Service 
Bulletin A310-28-2178, Revision 00, dated January 9, 2017 (for wing-
outer tank and trim tank fuel pump canister hood halves).

(k) Credit for Previous Actions

    (1) 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 paragraph (k)(1)(i), (k)(1)(ii), or (k)(1)(iii) of this 
AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; or Airbus Service Bulletin A300-28-0089, Revision 02, dated 
April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; or Airbus Service Bulletin A300-28-6106, Revision 02, dated 
April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; or Airbus Service Bulletin A310-28-2173, Revision 02, dated 
April 25, 2014.
    (2) This paragraph provides credit for the actions required by 
paragraph (h) of this AD, if those actions were performed before the 
effective date of this AD using the applicable service information 
specified in paragraph (k)(2)(i), (k)(2)(ii), or (k)(2)(iii) of this 
AD.
    (i) Airbus Service Bulletin A300-28-0089, dated January 13, 
2011; Airbus Mandatory Service Bulletin A300-28-0089, Revision 01, 
dated April 15, 2011; or Airbus Service Bulletin A300-28-0089, 
Revision 02, dated April 25, 2014.
    (ii) Airbus Service Bulletin A300-28-6106, dated January 13, 
2011; Airbus Mandatory Service Bulletin A300-28-6106, Revision 01, 
dated April 15, 2011; or Airbus Service Bulletin A300-28-6106, 
Revision 02, dated April 25, 2014.
    (iii) Airbus Service Bulletin A310-28-2173, dated January 13, 
2011; Airbus Mandatory Service Bulletin A310-28-2173, Revision 01, 
dated April 15, 2011; or Airbus Service Bulletin A310-28-2173, 
Revision 02, dated April 25, 2014.
    (3) This paragraph provides credit for the actions specified in 
paragraph (j) of this AD, if those actions were performed before the 
effective date of this AD using Airbus Service Bulletin A300-28-
6110, Revision 00, dated November 28, 2013.

(l) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Section, Transport Standards Branch, 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 Section, send it to the attention of 
the person identified in paragraph (m)(2) of this AD. Information 
may be emailed to: <a href="/cdn-cgi/l/email-protection#9aa3b7dbd4d7b7ababacb7dbd7d5d9b7c8dfcbcfdfc9cec9dafcfbfbb4fdf5ec"><span class="__cf_email__" data-cfemail="86bfabc7c8cbabb7b7b0abc7cbc9c5abd4c3d7d3c3d5d2d5c6e0e7e7a8e1e9f0">[email&#160;protected]</span></a>.
    (i) Before using any approved AMOC, notify your appropriate 
principal inspector, or lacking a principal inspector, the manager 
of the local flight standards district office/certificate holding 
district office.
    (ii) AMOCs approved previously for AD 2012-21-04 are not 
approved as AMOCs with 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 Section, Transport Standards 
Branch, FAA; or the European Aviation Safety Agency (EASA); or 
Airbus's EASA Design Organization Approval (DOA). If approved by the 
DOA, the approval must include the DOA-authorized signature.

(m) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) EASA AD 2017-0051, dated March 23, 2017, 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-2017-0714.
    (2) For more information about this AD, contact Dan Rodina, 
Aerospace Engineer, International Section, Transport Standards 
Branch, FAA, 1601 Lind Avenue SW, Renton, WA 98057-3356; telephone 
425-227-2125; fax 425-227-1149.
    (3) Service information identified in this AD that is not 
incorporated by reference is available at the addresses specified in 
paragraphs (n)(5) and (n)(6) of this AD.

(n) 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 18, 2018.
    (i) Airbus Service Bulletin A300-28-0089, Revision 03, dated 
December 16, 2016.
    (ii) Airbus Service Bulletin A300-28-0092, Revision 01, dated 
August 29, 2014.
    (iii) Airbus Service Bulletin A300-28-0094, Revision 00, dated 
January 9, 2017.
    (iv) Airbus Service Bulletin A300-28-6106, Revision 03, dated 
December 16, 2016.
    (v) Airbus Service Bulletin A300-28-6110, Revision 01, dated 
August 29, 2014.
    (vi) Airbus Service Bulletin A300-28-6114, Revision 00, dated 
January 9, 2017.
    (vii) Airbus Service Bulletin A310-28-2173, Revision 03, dated 
December 16, 2016.
    (viii) Airbus Service Bulletin A310-28-2175, Revision 01, dated 
August 29, 2014.
    (ix) Airbus Service Bulletin A310-28-2178, Revision 00, dated 
January 9, 2017.
    (4) The following service information was approved for IBR on 
November 27, 2012 (77 FR 64701, October 23, 2012).
    (i) Airbus Mandatory Service Bulletin A300-28-0089, Revision 01, 
including Inspection Findings--Reporting Sheet, dated April 15, 
2011.
    (ii) Airbus Mandatory Service Bulletin A300-28-6106, Revision 
01, including Inspection Findings--Reporting Sheet, dated April 15, 
2011.
    (iii) Airbus Mandatory Service Bulletin A310-28-2173, Revision 
01, including Inspection Findings--Reporting Sheet, dated April 15, 
2011.
    (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: <a href="/cdn-cgi/l/email-protection#355456565a405b411b545c47425a47415d1850544675545c475740461b565a58"><span class="__cf_email__" data-cfemail="d2b3b1b1bda7bca6fcb3bba0a5bda0a6baffb7b3a192b3bba0b0a7a1fcb1bdbf">[email&#160;protected]</span></a>; 
internet: <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (6) You may view this service information at the FAA, Transport 
Standards Branch, 1601 Lind Avenue SW, Renton, WA. For information 
on the availability of this material at the FAA, call 425-227-1221.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: <a href="http://www.archives.gov/federal-register/cfr/ibr-locations.html">http://www.archives.gov/federal-register/cfr/ibr-locations.html</a>.

    Issued in Renton, Washington, on December 4, 2017.
Dionne Palermo,
Acting Director, System Oversight Division, Aircraft Certification 
Service.
[FR Doc. 2017-26627 Filed 12-13-17; 8:45 am]
BILLING CODE 4910-13-P